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SILICA

HEAT SHIELD SIZING

24 JULY 1975 RI=PORTMDC E1343

FINAL REPORT4 MARCH1975TO24JULYt975

PREPAREDBY: _,9,_..._L. H. Ebbosmeyer, Engineer, ' "'Thormodynomics

PREPARED BY: '_" _' _

E. Chrlstensen, Senior Group Engineer, Thermodynomics

APPROVED BY-,- _ _ _R. V. Mosok, Monoger, Themnodynamics(Acting)

SUBMI'I'rED TO NASA/AMES UNDER CONTRACT NAS2-7897(REV 4)

MCDONNELL DOUGLAS AIrI'I, IONAUTICII COMPANY . EAII'I"

Saintc_,uis,Missouri63166 (314) 232-0232

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EAT IELDSlZIH6 I.o.T.ocFINAL REPORT 2,4JuLY 1975

FOREWORD

This report su_nnarizes the work conducted by HcDonnell Douglas Astronautics

Company-East (MDAC-E) in St. Louis, Missouri for the NASA Ames Research Center

(NASA-Ames) under Contract NAS2-7897 (Rev 4), "3ilica Heat Shield Sizing." The

period of performance was from 4 }/arch 1975 thru 24 July 1975. i

This study was performed under the direction of H. K. Larson of NASA-Ames.

Significant contributions to this study were made by H. J. Fivel and T. W. Parkiuson.

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EAT SHIELDSIZlN6 J REPORT.0¢ E1_43FINAL REPORT 24JULY1975

TABLE OF CONTENTSPAGE

11.0 L_TRODUCTIONAND SU)_AR¥ o o . . ° . o . . . . . o . ..... • ° . o •2

2.0 THERMALMODELS, . . . . ..... . . .......... . • . . . . •

3.0 E_TRY ENVIRONMENT..... . ..... . .............. .54.0 INFLUENCEOF HEATINGDISTRIBUTION IN THE GAP ..............

• 4.1 Heating Distributions in the Gap ................. 55

4.1.1 R.I. Baseline Heating Distributions ....... . ....

4.1.2 Gap Heating Correlation, Equation 4-17 ....... . • • • 56

4.1.3 Effect of Gap Heat Load ..................6

4.1.4 Ma_ssdorf Gap Heatin$ Curves ................6

4.2 Comparison of Heatins Distributions and Gap Temperatures .....

4.3 Tile Thermal Responses ................... • . • 7 _,_8

5.0 INFLUENCE OF TPS CONFIGURATION VARIABLES ............ . o . •

5.1 Tile Coating and Primary Structure Effects .... • • • • . • . . 8 _i8

5.2 Gap Width Effects ..................... . • • •8

5 3 Tile Edse Radius Effects• • • • • • • • e • • • • • • • • • • • • •

i6°0 ANALYSIS OF 0.157 CM RADIUSED TILES TESTED IN THE AMES 20 MW I

!TURBULENT DUCT ............................ o 10

7.0 CONCLUSIONS AND RECOMMENDATIONS .............. • .... ° 12 i

I

8.0 REFERENCES ........................ . ..... . 14

DISTRIBUTION LIST ........................... 58

APPENDIX A PRIORITY CASE LIST ......... . ..... o .... . A1

APPENDIX B TEMPERATURE-TIME PLOTS ................... B1

APPENDIX C THERMAL PROPERTIES ............... o ..... C1

LIST OF PAGES

Title Pase

li, iii

i thru 59

A1 thru A8

B1 thru B52

CI, C2

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1.O INTRODUCTION AND SUMMARY

The high temperature reusable surface insulation (_ESI) thermal protection

_ system (TPS) for Space Shuttle requires gaps at HRSZ Joints to accommodate struc-

tural deflection resulting from loads and thermal expansion. In addition, allow-

.... ance must be made for manufacturing and assembly tolerances. At room temperature,

sap widths under current consideration range from 0.05 inch to 0.10 inch. In

'_ orbital operation, these saps may shrink to near zero during cold soak and then

Stow by as much as 25Z during reentry. Candidate tile edge radii range from 0.03

_" inch to 0.10 inch.

The successful application of HRSI material for Shuttle thermal protection is

• sisnificantly affected by heating in the gaps between HRSI tiles durin$ entry into

• tl_e earth's atmosphere. Gap width, gap depth, tile edge radius, gap c_ose section

geometry, gap orientation, waterproof coating thickness, emittance of this coating,

! _ ' substructure, boundary layer state and surface mismatch are all known to affecti "

;i convective heating within the gap and heat leakage to the protected substructure•

! The objective of this study was to determine the sensitivity of silica heat

" shield requirements to gap width, tile edge radius and heat transfer distributions-

within tlle saps using representative correlations contalned In References 1 and 2.

::" Ocher information pertinent to the study was supplied by NASA Ames. For purposes

: of sensitivity studies the nominal configuration was specified to be a 6" x 6"

tile with a .I0 inch gap between tiles• Tile edge radius was specified to be

•06 inches. The two-dlmansional thermal model prepared for Reference I was

..- modified and used to determine the effect of two-dimenslonal heat transfer dlatri-

butlons at HR_ edges on Shuttle TPS requirements. For the Rockwell baseline gap

heating distribution the HRSI thickness requirements may be increased approximately

•! ,. _O% above the thickness required for a TPS with no saps in reBtonu of high heating

: on the orbiter lower surface•

;- This report also describes the sensitivity of TPS :_quirements to coating

: Llllckness, emissivity, substructure thickness and changes in gap heating for

i :_uveral locations on Shuttle.

'7 In order to better understand the effect of tile edge radius on TPS require-

ments, an inverse solution technique was applied to temperature data obtained in

; the Ames 20 MW turbulent duct. The derived heating values were then used to pre-

! dtct TPS requirements• The results of this analysis, summarized in Section 6.0,

' show that increasing tile radius reduces TPS requirements.

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I ", 2.0 THERMAL HODgLS

The Shuttle thermal protection system (TPS) consists of 6 in x 6 In tlles of

- L_-900 sillca High Temperature Eeusable Surface Insulation (HRSI). The tlles are

bonded to a thln strain isolator pad (SZP) which is in turn bonded to the primary

aluminum structure. The tile thickness on Shuttle varies wlth location; the thick-r ,.

hess being designed to limit the prlma_ry st_xcture to 350°F. The aluminum struc-

ture reaches maximum temperature after entry, during the period of heat soak. The

,. nominal TPS configuration employs tiles with corner edge radii of 0.06 In. and a

._.._" gap width of 0,i0 in. between tiles. The LI-900 HRSI has a density of 9 PCF and

is covered with a silicon carbide waterproof coating,- isi-

' TPS thickness requirements were computed for Shuttle entry trajectory 14414

at four locations deslsnated as Body Point I, Body Point 2t Body Point 3 and the•' q

. Body Flap. Body Point 1 corresponds to body station 1040 which is located near i

: the nose and reaches a radiation equilibrium temperature of 2335°F.' Body Point 2 i

: represents conditions at the fuselage midpoint (body station 1070) which reaches

• a radiation temperature of 1815°F. Body Point 3 is typical for aft fuselage "

!_ (body station 1157) and reaches a radiation equilibrium temperature of II80°F.

The Body Flap (body statlcn 212) reaches a 267YF radiation equilibrium temperature.

L-:" Transient temperature analyses for the complete trajectory were performed using

the two dimensional thermal model as shown on Flsure I. Computations were per-

• f_rmed for each set ofcondltlons until the aluminum structure reached its maximum

:._ temperature. The model uses hallmark dimensions such as V(2) to define key dlmen-

= ..... slons from which the remaining node dimensions are computed. The baseline conflg-

: uratlon is shown In Figure i. _l

:; To determine the temperature response resulting from a complete absence of gaps,

a one dimenslonal model was constructed. Thls model Is shown on Figure 2.

Consideration was glven to the need for assessing three dimensional heat

_'_ transfer effects. Slnce the available resources precluded analysis using a detailed

three dimensional finite difference computer model_ the two dimensional model was

: converted to a pseudo three dimensional model as shown on Figure 3. This method

assumes that the heatln8 conditions over the top of the tile was uniform and heating i

" in the gap was _wo d!menslonal and isometric. The heat storage terms were modified

as indicated in fihe Figure.

The influence of thermal models on TPS requirements is shown on Figure 4. TPS

thlckness requlrements for a two dimensional model which Includes gap heating are!¢

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15% greater than the one dimensional requirements whereas the three dimens_onal

model requirements are 30?. greater. The heating enviroument, SIP and structure at

body station 1040 was used for this analysis. The effect of thermal model differ-

ences on the body flap (B.P. 212) TPS thickness requtremen'_s, Figure 5, is lower

than for b_dy station 1040. The thickness increments are 4°3?. and 8.2?. for the

two dimensional and three dimensional models respectively. Figure 6 shows the

variation of maximum structural temperature with HRSI thickness for the one, two

and three dimensional models at body station 1040. In spite of the significant

difference bet_eeen the two dimensional and three dimensional predictions of HRSI

thickness requirements, differences in surface temperature between the two models

are shown in Figure 7 to be generally less than IO°F. Figure 8 shows the rapid

decrease of computed TPS thickness requirements with increasing width of the two

dimensional model. Also shown is the thickness requirement for a 6 in. _ 6 in.

tile computed using the Pseudo three dimensional model. The figure tndica_es that

three dimensional effects are important and that the TPS thickness is a gtrong

function of the ratio of gap length tQ tile surface area. Zt is also evident that

the required tile thi, ",_ese (hence TPS weight) could be reduced by increasing tile, size,

The majority of the analysis contained in the report employ the two-dlmenslonal

model as a consistent basis to show sensltivltlesb

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3.0 ENTRY ENVIRONMENT,.!

A current Shuttle baseline reference heating rate history is shown on Figure

9 for Shuttle entr? trajectory 14414 (Reference 2). Rearing rates for each of the body

points analyzed in this stu_ were computed by multiplying the reference heating rate

": history by a constant _atio of local-to-reference heatins rate (qL/qqEF). The

; local heatin8 rate was imposed on the top of the tile with the gap heatins dlstrl-

bution applied to the gap walls. The local pressure, Fisu_e 10_ on the Shuttle

_': lower surface was used to _taln the proper thermal conductivity of LI-900 which;..,, I

• is a function of both pressure and temperature, t. i

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"" 4.0 INFLUENCE OF HEATING DISTRIBUTION IN THE GAP

,:, Extensive arc and wind tunnel Casts of instrumented panels of t;ileshave been, -o

performed in order to quantltize the heating distribution on the fa,_esof the tiles.

Various correlations have been developed to describe the distributioDs in the gap.

• Three general correlations wets already developed at the start of this study and a

fourth was developed by this study (see Section 6.0)° The characteristics of the

• first three correlations and the resulting impact on TPS requirements and thermal

....i responses are contained in the followlng subsections.

4.1 Heating Distributions in the Gap - Comparisons were performed using the ..

"R.I. Baseline Heating Distributlon", _he "Gap Heating Correlatlon, Equation 4-i_"

_, and the "Marssdorf Qurves".

: 4.1.1 R._I.Basellne Heating Correlation - At the outset, TPS _equlrements

: were computed using only the Rockwell International baseline (R.I. B/L) heating

_. distribution in transverse gaps as shown on page 16 of Reference 2 and shown here

,: as Figure 11. This curve was originally developed for a gap width of 0.i0 inch

and a tile edge radius of 0.06 inch. However, to deterntlne the effect of varying

_ gap width and edge radlusp this distribution was used for several combinations of

_"- Width and radii. When using this curve the results show a slight increase in

:" requirements with increasing gap width, and a decrease in TPS requirements with

i:. increasing edge radius.

4.1.2 Gap Heat£ng Correlation m Equation 4-17- A gap heating correlation

.:. (Eq. 4-17) for a transverse gap, was developed from data measured on thin skin

_" tiles with various edge radii and gap width settings. The model was tested in a

": wedge in the JSC i0 MWArc Tunnel_ The data analysis and correlation are reported

: in _eference i. Figure 12 summarizes the heating data obtalned in transverse gaps

with superimposed plots of the resulting correlation equations. The correlating

_. equation is presented in _igure 13 together with the regre_iOD correlationo.!'

coefficient, standard error of estimate, minimum and maxlmumheatlng for both the

'". measured data and the derived function.

As can be seen from Figure 12, the heating data do not extend deep into the

!i- _ap. Figure 14 shows the method of extrapolating the correlation curve toward the

.'i," oondline. In the gap near the upper surface a second order curve was fit tangent

: to Equation 4-17 and passing through £n(q/qFp) - 1.0 at the tangency point of the

edge radius and tile flat surface (S=O.O). (The extensions of Equation 4-17 used.,o

_i. in the vicinity of the tile corner are show;L in Figure 12.) The technique of

, extending the correlation curves is described in Section 6.O of Reference i.

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4.1.3 Effect of Ga_ Bea_ Load - Figure 15 contains transverse gap heatin&

f distributions for a tile with an edge radius of 0.06 inches and a gap width ofi

I 0.10 inch between tiles based upon several computational methods. Method 1 is

t the R.I. baseline heating distrtoution. This distribution requires 3.32 inches

of HRSI in order to limit structure temperatures to 3500F. Computer runs ware

i i made using 3.32 inches of HES_ in order to determine how the other methods would

: . affect the maximum structural temperRture. The temperatures ranged from 354°F to

427°F. Also the TPS thicknesses required for each heating dls_rlbutlon to satisfy

the 350°F limit were computed. Figure 16 shows the effect of integrated gap heat

load on HRSI requirements for a 5.0 x 6.0 inch tile. Method 3A requires approxi-

• mately 31% more HRSI than Mothod i. Comparison of HRSI requirements from Methods

3 and 3A, Figure 16, show that the lack of accurate definition of heating at

q/qREF _ 0.i, which occurs deep within t_e gap, can significantly affect the TPS

thickness. Sensitivity tq heat load on the body flap is also shown on Figure 17.

Method 3 requirements for the flap are approxlmately 16_ greater than Method I.

4.1.4 Marssdorf Gap Heating Curves - Heating distribution curves for a trans-

_ verse gap developed by J. Marssdorf of Rockwell International were furnished by

F. J. Centolanzi of NASA-Ames. These curves were derived from tests using thin

.. skin tiles having a 0.i0 inch gap and 3 different .edge radii. The heating curves

; were derived a¢countlng for thermal conduction effects. The tests were conducted

in the JSC 10 MW Arc Tunnel.

The curves of Marssdorf are plotted in Figure 18 as a function of "Z" (dis-

tance into the gap measured from the tile top surface). This figure shows a

significant affect of tile edge radius on gap heating o%strlbution. Analyses

employing the Marssdorf curves are contained in subsequent sections.

* 4.2 Comparisgn 'of Heating* Distributlons_. _and__Gap Temperatures,_ - Figure 19

shows additional heating distributions for a .10 inch transverse gap with tiles

'_ having an edge radius of 0.06 inches, The curve labeled Equation 4-17 "her.e'and -

on Figures 20 and 21 was used for obtaining the effects of edge radius and gap

widths on TPS sizing. The Marssdorf curves al_d the revised R.I. Baseline (data

, from Ames Aero Heating Test No. 158) heating distribution prepared by Marssdorf

are shown for comparison. A table of F_gn_e 19 shows the percent change compared

_ to the R.L Baseline. Figures 20 and 21 show the comparison of MDAC Equation 4-17

_ and Marssdorf curves for tile edge radius of .12 and .25 inch respectively. The

two heating distributions for a tile having a large (0.25 inch) radlus are very

simiIar.

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The heating dtscributione £or wirioue edge radii _omput_d u_i_g the _LDAC

Equation 4-17 nre _ompnred in FCgure 22. A similar _omparison is m.de in Figure

18 using the curve fits obtained by 14arssdorf, The level of heating increases when

increa_ing the edge radius on both f£gures, Figure 18 shows a 8_eater spread for

edge radius range than does Figure 22. Even though the heating increases with in-

creasing edge radius, the temperatures within the gap decrease with increasing edge

cadius for Equation 4-17 as is shown in Figure 23. With large edge radius more sur-

face is available for radiation to space (T - O°R), thus increasing the heat rejected.

However, as shown in Figure 24, the Marssdorf distribution results In increasing

gap temperature with increasing edge radius. In this case there is a sufficiently

large increase in gap heating with increasing edge radius that the c:onvectlve heat-

ing out weighs the radiation effect. Figure 25 shows the temperatu3_es for the

Eockwell International baseline heating curve andtheMarssdorf revision to that

heating curve.

4.3 Tile Thermal Responses - Typical temperature-time history plots in Figures

26, 27, and 28 show the response o_ the tile, the coating on the tJ.le top and gap

wall, and in-depth temperature near the center of the tile. Temperature-time plots

are presented for 17 priority cases in Appendix B. Figure 29 Is a typical temper-

ature isotherm plot at the time of peak heating showing that the in-depth temper-

atures of the coating in the gap and temperature_ in the HRSI adjacent to the gap

coating are hotter than the in-depth temperature of the HRSI toward the center of

the tile. This figure shows the extent of the effect of gap heating on temperature.

The sensitivity of aluminum temperature to tile thickness is shown in Figure

30 for a nominal gap width of 0.10-inch and an inner edge radius of 0.06 inch.

For reference purposes, a one dimenslonal thermal analysis at the same vehicle m

location, indicates a _quirement of 2.88 inches of H_I. Information from the i

iprevious figure is also presented in Figure 31 in terms of an increase ove_ the

one dimensional value,_ Using the heating distribution of Equation 4-17, approximately

33_ more HR$1 is needed considering a nominal gap and a maximum aluminum temperature

of 350°F. By referring to Figure 31 and choosing other maximum aluminum temperatures

the percentage change over a I-D model is easily obtained.

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5.0 INFLUENC_ OF TPfl CONFIGURATION VARIABLES

In addition to convective heating_ the TPS requiremente are 8overned by heat

t_ansfer characteristics o£: the nRflI, the fliP, the tiIe coating and the primary

structure. Gap width and tile edge radius also enter into determining TPfl require-

ments. _?he senslclvlty of TPS requlrements to configuration varlablu_ are analyzed

in th_ following subsections.

5,1 Tile Coatins and Primary StFucture Ef£ects- The effect of HRSI _oatin_

emissivity and aluminum structure thickness can be seen on Figure 32. The one

dlmenslonal thermal.model has coating on the HRSI surface only, while the two

dimensional model has the coating on the gap walls as well as on the surface. For

the emissivities and thicknesses used for this figure, the ratlr of 2-D to 1-D

model TPS requirements change only slightly. Changing the aluminum structure

thickness from 0.08 inches to 0.12 inches reduces the 2-D TPS requirement by

_roxlmately 17 percent.

The HRSI coating thickness also affects TPfl requirements. Figure 33 shows

t_at changing the coating thickness from 0.005 inch to 0.025 inch increases the

2-D requirements by three percent. This increase is minor compared to the gap

width and edge radius effects. The coating has an order of magnitude higher con-

ductivluy than the HRSI.

! 5.2 Gap Width Effects- The effect of gap width on aluminum structure temperature,

using the heating dlstr_hut_on curve of Figure ii is shown on Figure 34. A more

realistic effect of gap width is shown on Figure 35whlch was derived by using

F_AC correlation Equation 4-17 (Reference i). This figure shows the effect on TPS

requirements for various gap widths and edge radii. Figure 35shows that increasing

the gap width from 0.10 inch to 0.20 inch results in a tile thickness increase of

seven percent for a tile with an edge radius of 0.06 inches. Figure 36 shows the

same information normalized to the 1-D thermal model requirements.

5.3 Tile Edge Radluu Effects- The tile edge radius also has an effect on TPS

requirements as shown on Figure 37e First, analysis were performed assuming that

the heating distribution with respect to (Z) did not change and only varies with the

geometry of the tile edge. The heating curve in Figure ii was used. The TPS

requirements drop for increased edge radii for all three body points (See Figure

37). Analysis were also performed using the HDAC correlation Equation 4-17 which

accounts _or edge radius (See Figure 38). Increasing the tile inner edge radius

from O,06 inch to 0.12 inches reduces the required HRSI thickness by about 0.2

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• inches (or fivv percent) for a gap width of 0.10 inch. Figure 39 show_ thl_ same

information normalized to the I-D th(_rmal model requlrement_.

Three other gap has,in8 distributions wer_. _nvestigated to deto.rtaine edge

radius c£fects on TPS reqttirements. They are shown on Figure 40. Uflin_ the

M_ir_sdor£ heating distribution ,mrvea Indicates the TPS requirements ln0rcase with I

increasing the edge zadius. Heating distributions were also obtaine_ fat IIRSI tiles !

(0.06 and 0.25 inch edge radius) tested in the Ames 20 MWTurbulent Duct, _ :ng O_ i

da_ from the Ames 20 MW Turbulent Duct Facility for tiles with a 0.06 inch _nd O. '5

inch edge radius and having a 0.?.0 inch gap width, t_le 2-.D requirements ._nc.._,_

by approximately 25 percent and 9 percent respectively over the ]'.._ , mal ,. .,;..

re,luirements but are less than that required using the o_' .... .xons. These

results show the same =rend as Equatio_ 4-Z7 heating dir'._ LbJ.ion when varying

edge radius.

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. - 6.0 ANALYSISOF 0.157CM RADIUSHR3ITILESTESTEDIN THE AMES_ 20 MWTURBULENT DUCT

_" Durln8 the course of this contract, thermal response data for a series ofJ.

Arc Tunnel tests of 0.157 ca radius silica HRSI tiles tested in the Ames 20 MW

•, Turbulent Duct ware received. The test panel consisted of an upstream tile and a

downstream tile positioned to form a transverse gap tested in the wall of a duct

through which turbulent air flowed from an Ames 20 MW Arc Heater. A series of six

" tests were performed which were a companion test program to that performed on a

_ set of 0.635 cm radiused tiles reported in Reference I.

The 0.157 cm radius tiles weT_ instrumented with thermocouple s on the top of the

tile_ down both faces of the transverse gap and also in-depth. Tests were conducted with

each tile being in the upstream posltlon so as to get comparative data to ascertain

the effect of tile instrumentation on derived gap heating. Heating rates were

calculated by the "Inverse Solution Technique" (described in Reference 3). This

; technique utilizes a detailed thermal model of the tile test panel and the measured

;_- temperature histories in a transient analysis to determine heating rates. '

:. Derived Gap Heatin 6 Distribution for 0.157 cm T_le Tests - HeatlnE distributions

were calculated for the downstream wall of the transverse gap for three gap widths

(0.12 7, 0.254 and 0.381 cm) with thermocouple (T/C i) being in the'upstream and in

the downstream position. The calculated heating distributions are contained in

_,_ Figure 41. The spread in heating value attributed to instrumentation and test

conditions is reasonable as evident upon examination of this figure. Data fairing

was used to obtain an experimentally derived heating distribution for each gap

: width and the effect of gap width is evident in Figure 42. The convective heating

drops off with distance into the gap and the heatln 8 intensity increases with

_: the gap width. The shape of the heating distribution should be noted_ because of

a slight plateau z_ear the top of the gap. Uncertainties in coating thick-

hess, surface emittance and coating conduction effects become significant below a

depth of 0.7 cm where the convective heatin_ becomes negliglble. The heating ratio

.... measured near the top of the gap(for a gap of 0.254 cm)is comparable to what wa_.obtalned ....

in the LaRC CFHT facility. The results for the narrower gap (0.127 cm) are com-

'i parable for 0.178 cm gap _ested in the LaRC 8 Foot HTST. These other facilities

also p_oduced turbulent flow and the referenced heating distribution are contained

in Figure 161 of Reference 1. '

, The heating distributions obtained for the 0.157 cm and 0.635 cm radlused HRSI

tiles are compared in Figure 43. As can be noted from the figure, increasing the

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i,' edse radius siani£icantly reduces the convective hearths within a transverse sap.

-- Also the required tile thickness is also alani£icantly reduced by tncreas:Ln8 the

"_ edae _adius (See Section 5.3, ¥taure 40).

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7.0 CONCLUSIONS AND RECOMMENDATIONS

In this study the sensitivity of the Shuttle HRSI thickness to various design

parameters has been investigated. The design parameters which were investigated

include tile edge radius, gap width, gap convective heatln8 profiles, alumlnum

substructure thickness, and tile coating thickness. Figure 44 summarizes these

• results which are predicated on limiting structural maximum temperature to 350°F.

Heating distributions were derived for the 0.157 cm radlused HRS[ tiles tested

in the Ames 20 MNTurbulent Duct Facillty.

Following are some of the major conclusions derived from this study:

: I. Based on HRSI Turbulent Duct Tests, increasing tile edge decreases con-

vective heating in a transverse gap. This finding is in contrast to

results obtained from thin skin model tests conducted under laminar flow

conditions where convective heating increased sllghtly with edge radius.

2. Increaslns tJ.leedge radius appears to reduce HRSI thickness requirements.

--. This conclusion is sensitive to the manner in which existing experimental

heat transfer data are interpreted, and using other Investlgatorts heating

distribution results in contradictory concluslons.

3. A significant decrease in TPS thickness (as well as a reduction in tile

inventory) would result from increasing HRSI tile size.

4. Increasln8 gap width from .i0 to .20 inch increases the HRSI thickness

requirement by 7_, prlnclpally as the result of increased gap convective

• heating.

5. The HESI thickness requlrement5 decrease as the aluminum structure thickness

(or heat capacity) increase. _or example, a change in aluminum thickness

of 50_, from 0.08 inch to 0.12 inch, results in a 17Z reduction in required

HRSI. However, such a change actually results in a 4X combined weight increase.

. 6. Coating thickness has a minor effect on HRSI thickness required compared

": with the effect of other parameters. A 3Z increase in HRSI thickness

requirement results from increasing coating thickness from 0.005 inch to

0.025 inch. The increased HRSI thickness occurs because the coating

thermal conductivity is an order of magnitude higher than that of the HRS1.

_ 7. The precision (or lack of precision) to which the convective heating

distribution down the face of a gap is knownm dlrectly in£1uences the

" required amount of HRSI. Even the low convective heatln& (0.01 _ q/qRef

_ 0.I) which occur deep within the gap result in direct heatin& of the

lower portions of the gap and hence.increase TPS requirements.

-" MCDONNELL DOUGLAS ABTRONAUTIC8 COMPANV . EABT

_7-_= _ _- .................................................o

.... 00000001-TSB08

I •,e i • .i L t

t

, _EAT SHIELO|lZlN6 I REPORTMDCE1343:.. _ FINAL REPORT j 24 JULY 19;S

8. Temperature in the coaCin& at the HRSZ/RTV bondllne near the tile edse

r can be approxlmacely 30°F steerer than the HRSI/RTV bondllne at the

center of the tile. Thl8 ipcrease in temperature is a comblnation of the

hIsher conductivity in the coating and convective heatlnS in the sap.

9. Temperatures on the 0.060 inch radius portion of the tile may exceed

.i.:_ _ smooch surface temperatures by as much as 129°F.

' i0. The HRSI thickness for a 350°F bondllne (usin8 the R.I. baseline heatln 8

distribution for a 0.06 in. radius tile with a 0.10 in. sap) is 15 percent

._ greater for a two-dimenslonal model and 30 percent 8rearer for a pseudo

-=" three-dlmenslonal model over the one-dlmenslonal model requirements.

The following additional effort is recommended to maximize confidence in

.,:,-. the TPS desisn:

- _: 1. A sisnlflcant portion of the Shuttle TPS employs tiles orientated at

=i 45°. Consequently Arc Tunnel Te8t (both laminar and turbulent) of

i radlused HRS_ tiles should be conducted at several Kap orientations to

_, determine heaCin 8 patterns that can be expected durin8 flisht and to

_ study optlmum tile configuratlon. These tiles should be extensively

instrumented in the upper re$1ons of the gap ar,don the radlused region.

2. Analysis of the additional tests to obCaln convective heating race

,_ distributions. These _onvectlve heatlns race distributions should be

1" compared with prior work to evaluate the consistency of the test results.

-- i I I _

EAT SHIELDSIZING........ REPORT MDC E1343

FINAL REPORT 24JULY1975

8. 0 I_FEI_C_.

1. "Data Correlation and Analysis of Arc Tunnel and Wind Tunnel Tests of RSI

Joints and Gaps," Phase II ¥£nal PJeport, MDCE1248, 19 May 1975.

2. "Gap Heating Study Matr£x," supplied by H. K. Larson, NASAAmes, March 1975.

3. "Heat£n8 in Shuttle PSI Gaps Derlved from an Inverse Heat Transfer Solution,"

H. E. Chtlstensen and H. W. Kipp, ASME Paper 75-ENAS-15, July 24, 1975.

i . .o.c.o____......

&

00000001-TSB05

° .,.T._ _

_". _EAT SHIELOSIZING m REPORTMDC E1343"- FINAL REPORT 24 JULY 1975| ill

s

TWO-DIHENSIONAL THERMAL HODEL

_; OF AN HRSI TILE JOINT WITH EDGE RADIUS

L.. V(5) -'_ V(4)

_ V(2 V(932" 66 ', 05 '64

.:.... _ _u.+..... 't-- - "-(" T• bl Z ,,,, • i ,-: • 44

....: . . 9] " * 93 23 I" //,," •94."'i- ....... ', V(2)

.'-,,,.96 .24 i k,, .4s ::__ " 68 _, 92. /..97_ L. _ _ _ _ ; i-i-'L.Ejs.L913¥'99 • 25 I ,6

•,. t:' 69' 4 '100 ,j. 4.. '_, mm m m m m

_T, " 70- 5_. ..... .26 ! .47_ ,, 7|_ 0 .27 •48 'HRSI

I

- 72-.7_ .2e_ ...... _ ) .49 -. V(1)•' 73.- 0 .29 .50

- 74,.9 .3o ..- . 7_,-i_ ._1 .s2

_. 77* 12 .33. I .54 / "I" 78-. 13 .34 • 55 ;

79-. 14 .35 .56

: 80" 5 ,36 57 -_i vA;- .- 81- 16 .37 .58 .

. '* 82 - 17 .38 • 59

"..... " _ _.......... --4_--" . " - t':- "_'_o_.zi'o....... _T"" ,62

ALUMINUM 2 RTV

' ",eV(13)_'H STRUCTURE • SIP J:" ,. GAP..II_ 3.00 IN.WIDTH "71_F,,_COATING V(9)

• BASELINECONFIGURATION:

: I HEATINGDISTRIBUTIONIN GAP(R.I BASELINE)2. MODELWIDTH= 3.0 INCH

3. INNEREDGERADIUS(w)(EJ);HO.06 INCH %0_0_I_4. GAPWIDTH = 0.10 N !tli_t_UOl[B1Zw

5. COATINGEMISSIVITYlil - 0.80 _l_IA,lb 'J, ii'' 6. COATINGTHICKNESS( = 0.015 ItlCH: 7. ALUMINUMSTRUCTURE ,,0.080 IflCH- 8. SIP PLUSRTVADHESIVE = 0.175

l

" 15 FIGURE1

MCDONNELL DOUGLA# ASTROItlAUTICS COMPAItIV . I_ABT

............ :_

0000000"1-TSB06

i .....

_ "_ __LICA HEATSHIELDSlZIHG I REPORTMDCE1343FINAL REPORT 124 JULY 197.5

w

PSEUDO 3-D THERMAL MODEL OF BUTT JOINT

jma.p

• ,," 0 101 THERMALNODESt o CONVECTIVEHEATINGTO SURFACENODES

o RADIOSITYNETWORK,RADIATIONFROM.... SURFACENODES

o HEATSTORAGEAT NODESo CONDUCTIONLINKS BETWEENNODES

o SURFACENODES(43,22,1 TO 19)o CENTRALSTACK(NODES43 TO 63)

"," o INTERNALNODESAT EDGE(NODES90 TO 101).:_ o NODES22 TO 40, INTERNALNODES

HRSI 0 SIP NODES 88,101,19,20,40,41,61,620 STRUCTURENODES101,89,20,21,41,42,62,63

,,87 (RADIATIONSINK)

-- " _ 22 43 _COATING

--,,,_ _,, i• , 5 926 •J • •

I " •

: I • ,,P.--HRSI

I . ,

" I

r io, - •.. ---_.= 9 40 ...... 2 RTV LAYERS+SIP

.... 89 42 6"3 [- ALUMINUMSTRUCTURE: *ALL NODESNOTSHOWN

" 17 FIGURE3

MCDONNELL DOUGLAS ASTRONAUTICS COMPANt" * EABT

OOOOOOO1-TSB08

L

' ' _F.AT SHIELDSIZING I REPORTMDCE1343FINALREPORT 24JULY197S

m

INFLUENCE OF THERMAL MODEL ON TPS REQUIREMENTSi,!. •; • BODYPOINT1T • R.I. BASELINEGAP HEATINGDISTRIBUTION

i . " ..... • TRAJECTORY14414

4.0

Z -"mmm

i" ' ,;" I 30%,._" -- 3.0 i 15%

t/_ m _ _

b_

2.0

: Z

-- 1.0

I

: X !" 0 , , l f'_II I

-O 2-D 3-D,_,

.= THERMAL MODEL

;'--" |8 FIGURE4

J" ' MCDONNELL DOUOLAI ASTRONAUTICS CDMPANV . lAB?

U

NNAAAAAt _Te_nn

EATSHIELDSIZING _ REPORT MDC E1343FINAL REPORT 24 JULY 1975

INFLUENCE OF THERMAL M,ODEL

ON TPS REQUI REMENTS

• FLAP(BODYPOINT212)• R.I.BASELINEC_APHEATINGDISTRIBUTION .........• TRAJECTORY14414 ....

4.0

u')L/J

ZI,-,I

' 3.0

'_ m -'_8.2%"" m L4•3% :M,. i

LLtz 2.0(,,)

I

1.0

,

, 1-D 2-D _-D

: THERMALMODEL

19 FIGURE5 :

'MCDONNELL DOUGLA| A|TRONAUTICB COMPANV . |A|T i'

oooooooI'TSBIo

' i'. -- i I i i i ,

,I1 ,' _E_T _HIEL9SlZIN6

i"i!!!!!i!iliiii!!i FINAL REPORT j REPORTMI:)Ce13432,_JULY 197S

THERMAL MODEL INFLUENCE ONTEMPERATURE AND TPS REQU IREMENT

- SHUTTLE BODY PO INT i

TRAJECTORY 14414........ i

!

_EAT I REPORTMDCEI_,_

SHIELDSIZING

FINAL REPOr'T 2,1JULY 1975_l_-: . _]11

TEI,IPERATURE D IFFERENCES BETWEEN2-D AND 3-D THERMAL MODELS

• BODY POINT I• 0.I0 IN. GAP HEATINGDISTRIBUTION(R.I.BASELINE)• TRAJECTORY14414• 0.06 IN. EDGERADIUS• MAXIMUMALUMINUMTEMPERATURE= 350_F

22 FIGURE8

MCDONNELL rJOUOLAg A_I1PRO&IAU'JP'ICII COMPANV • EAII'r

+ .,

.......... 1 "+_ _,+.+Jl

O0000001-TSB13

I_. tilL*

ti

EATSHIELGSIZINGy,../ . FINALREPORTI RePQf_TMacEIs4]I 24 JULY 197'_

REFERENCE HE,_,I'IHGRATE /,

• TRAJECTORY14414 (REFERENCE2)

' 70 .....................

" .__

:;ii,/!ill!i::li2__-:..t::i,,!!

:, 60 il _!_i_._ii!i_.! Z BODYPOINTI (I040)

i!:_._iii:._::__i:,/.:i_i:ii::i!li_::%_.:_::.ii!._l:-:i;:..ili:.:.itiiiil:::,iii!i!!l:,_:.._i!

..... _ ,, _tl

_" ]]:I:;; • tl:it!!:.i::l_];]l::]:. i._]:Ii:::i,::.t.;iii::]:l;]]ii]]iit:!_ii!_!!_!ii;_i!i._L% ' '1''" _.,._' " ' ......................... '" "'l::::[::::l:-': I.L_ :! 1

:__-:.",.'_:_:i"-'_ ...._+/..-.._.-,7."'.,....,....,.:..,....,...:,...

"'._ "."" '?" _:'"_ ...z . ..- " _,..'_..-[:: "'.'.. . ::; : : . " : -...':: • .

• " • 1 • • '. , • -t'_:_ }_: t,. ";'_. - ]',_J.;..... _..... l •

•o_" ::ii:::.,._:,:::'::_:.'_::i ........'_'.:_'.!':_.i:!-.I!!! !_!!t_i!!_:!:L:!!:_!iiii-.!

.... : ::1 _! i::/i iil I:L!II I:.,,:,:,_1:T:,i!:._!_::,:,t:,._i:ii:,:iii:!!!!i.i,,'_ " ' .... I .........

......... -_-'..L.;, : :!

" ' _ "-" .i :. _ ..... '_ i_i_.,:"i ....::...,..h i_ ..............'................

.: _. . _ .I, • _ ...I......

:::!::::t::!:t:: it!!:::::'it!: !ii!:. !: '20 • _. , , ... : ...._,. :. :.i...... _................ t......... i,

_TU/_T_' ......_:....: ...... :... QLCADREF= 512BB :i:.iiiiii_:.iii:.!Ei:.:.lii!:,:.iF.l:.:-i_

' _:I:_iilill' _ BODY POINT I (1040) _IL/_IREF= 0.3646_iiF_!i_' !:,L_ . "": BODYPOINT2 (1077) q./o... 0.1618 ..::i::.:,::::_... ,::: ,:: i! __. t. K_P _::::I:::: ::::: " :::t:::. BODY POINT 3 (1157) _L/_ +: "_,' ':.: .... ,.... ,.... ,_. :... _ ,...... ,,.,;.....,..,,__..:....: :._!ii_!:::! ii_i:;._ ...... i_..........

0 400 BOO 1200 1600 2000 'TIME - SECONDS )

• 23 FIGURE9

' M_.OON_I_'LL DOU#JLAS ASTI_ONAU'IrlCS COMPANY. _EAI1P

O000000"I-TSB'I4

,'.r .,

ATSHIELDSIZING

I REPORT MDC E1343r FINAL REPORT 24 JULY 1975

..... TRANSVERSE GAP HEATING DISTRIBUTION:i.i--.. ROCKWELL INTERNATIONAL BASELINE:- 0 ,06 INCH EDGE RAD IUS-O ,10 INCH GAP W IDTH

• REF: AEROtlEATINGTESTNO. 158:. - AMES 3.5 FOOTWIND TUNNEL,: CONDUCTIONCORP_CTEDDATA

"" 1.67

_. 1.4

• _[

1.2

.... a_

_- 1.0

.,: _ .8. . mm I":.'i

a,.

: .6

.4

0. 0 .'1 _, .2 .3 .4' .5 £

Z - GAPDEPTH- I_CH

- f 25 FIGURE11

' r' _ MCDONNELL DOUOLAS ASTIIOIIIAUTICIB COMPANY. II[AIIT

00000001-TSC02

!

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_., _EAT SHIELDSIZING I REPORT.DC e1343- FINALREPORT 24JuLY1975

[++!-. !i% 1

'J" _ l

e .-.=_ o_g_ ,..._=_:-=

U II # M _,_ • OI I II t-,

]?tI .... • ............

_+": 27 FIGURE13,l • MC_ONNE[LL OOUOLAS AS'O'O_ONAU'F#_S COMPANV . EAdDT

0000000 ] --T$C04

• • _ o , 4 l

1f

--.qFINAL REPORT REPORT MDC E1343:. 24 JULY 1975

: TECHNIQUE FOR EXTRAPOLATING

: ,/ CORRELATION FUNCTIONS

_-_. i,.° --. . i _o___T_,__Do_o__

FUNCTION,TANGENTAT A AND_" PASSESTHROUGHI.• ZONEB FIT ..............

: SLOPEOF1 CYCLE!_ PER0.5 cmFROMZNAX

..... _ . TOBOTTOMOFGAP

e "4,INSTRUHEr_TATION___ "

% ,

ZMIN ZMAX

Z ORS (DISTANCEINTOTHEGAP)

I

_'8 FIGURE14

MCDONNELL DOUGLAS; ASTRONAUTICS COMPANV . EAST

m_

T

O000000i'TSC05

I

_,A,.,<.,z.o ,.,<""o"I"''''°<'''2°_,.| •

EFFECT OF GAP 'IEAT LOAD ON• B"DY FLAP TPS REQUIREMENT

e FLAP (BODYPOINT212)

,.:. • TRAOECTORY14414• GAP_IIDTH" 0.10 IN.

• INNEREDGERADIUS= 0.06"

• MAXIMUMALUMINUMTEMPERATURE= 350°F

_EAT I R_:PORTMDC_1343

SHIELDSIZIH6

FINALREPORT _4JULY197S• , II

TRANSVERSE GAP HEATING DISTRIBUTION

USED FOR TPS S IZ ING_,'

REpI_DUCIBILI'_'"""e J. MARSSDORFIR.I.CURVE FIT OF -.....,

• C, SCOTTTESTDATA,_ISC10 MWTUNNEL _lilt,lllKN/dr,l)'S-G]_IB P_L_':.''• GAPWIDTH= 0.10 IN,

1.6 itII

1,4 !

.4 III{l

00 ,1 .2 ,3 ,4 .5 .6 ,7 .8

Z - DISTANCEFROMSURFACE- IN,

32 FIGURE18

MCDOIWNILL DOUOLA| AITIIONAUTICI COMPAItlV _,|AIT

00000001-TSC09

_EAT J REPORT MDC EI343

SHIELDSIZING

FINAL REPORT 24 JULY 1975

GAP HEATING DISTRIBUTION COMPARISON

• 0.10 IN. TRANSVERSEGAP OI¢IBI_F_ ¥&vm m J.,,-."• 0.06 IN. EDGERADIUS

1.6 MDACCORRELATION/EQ.4-17 t C. SCOTTTEST,.I.MARSSDORF/R.I.FIT JSC l O MW TUNNELR.I. BASELINE,CURVE7/22

1.4 AMESAEROHEATING--- REVISIONOF RoI. BASELINE

BY d. MARSSDORF,CURVE8/14 TESTNO. 158

iiii -fl F'-

1.0 ::;;DISTRIBUTION TESTARTICLE X-HRSI

RSI 3.32" 1.00

o. THIN SKIN 3.82" 1 15I,I. .8

=" THIN SKIN 3.33" 1.00

o" RSI 3.18" o.g6LEU

!;11!!!!

L]ll

rNrLIII

,1_!

!i!

.2 N;Htlf-ILL

0 .1 .2 .3 .4 .5 .6 .1

Z - DISTANCEFROM SURFACE- IN.

33 FIGURE19

MI_DOItlRIELL DOUGLAS ASTRORIAUTI_B i_OMPAItlt" • BAB'I _

O0000001-TSCIO

t

I

EATSHIELDSIZING J REPORTMD__lJ4J- FINAL REPORT 24JULY1975

• SURFACE, EDGE RADIUS ANDALUMINUM STRUCTURE TEMPERATURES

• BODYPOINT1' • TRA.]ECTORY14414

. • GAPWIDTH='0.10 IN i• INNEREDGERADIUS= 0.06 IN

"" QI " "

o o- o NgDES

I_ 43

_ 22N- 2'- 8

.4

_ 1t3

3 2 22 43I a ,

o "-"COATINGo co 7' *49

I

RSI

_°°_.=,,o_,,- 1111s .s3s7

° // 63SIP+ RTVADHESIVE

"---ALUMI,IIUMSTRUCTURE !

o o0 500 I000 1500 2000 2500 3000 3500 4000 4500 5000

_ TIME " SEC

40 FIGURE26

1 MCDONNELL DOUGLAS ASTRONAUTICS COMPANV. EASF

J REPORT MDC E1343 '_'_ ! FINAL REPORT 24 JULY 1975 . ,

!

TILE TOP AND GAP WALLCOATING TEMPERATURES "i

• BODYPOINT 1• TRAJECTORY14414• GAPWIDTH,,0,10 IN• INNEREDGERADIOS= 0.06 IN . l

•¢ o ii,,!

.... _ . • . ]

NeDE8o 22 '

2'- 3

4 ,.!o 7o IIo- 15III

2__22 47

o- .... 'I ""

===e. I R_, "laJ _

.............. 57,-. . _ 61-----

"¢ _ SIP + RTV ADHESIVE"-- ALUMINUMSTRUCTURE -_

0¢%1

0, ¢ ..........

0 500' I000 1500 2000 2500 3000 3500 4000 4500 5000"TIME " SEC . -.

41 FIGURE27

MCDONNELL DOUOLAr._ AETRONAUTICI COMF'ANV • IAII*

, Lt L,

! k' '" ""

+

00000001-TSD04

. __AT smL.=zm I' REPORT MDC E1343

FINALREPORT 24JULYle7s

: RSI IN-DEPTH TEMPERATURESNEAR CENTER OF TI LE

• BODYPOINT1• TRAJECTORY14414

. • GAPWIDTH=0.10 IN• INNEREDGERADIUS= 0.06 IN

0 500 I000 1500_2000 2500 _3000 3500 4000 4500 5000 ,--TIME " SEC

42 FIGURE28

Z-- _ - _ MCDONNELL DOUGLAS ASTRONAUTICS COMPANV . EAST

"41oo(_(_r)r}r_l _T._ r_n_

' REPORTMDCE1343' FINAL REPORT 24 JULY 1975

- TEHPERATURE ISOTHERMS THROUGH HRSI TILE.- • MAXIMUMHEATING(t = 500 SEC).. • BODYPOINT1 * * R.I. BASELINE._, • 0.10" GAPHEATINGDISTRIBUTION:. • TRAJECTORY14414 PRIORITYC_,SE7

• 3.32 IN. HRSI- :, _ • 0.06 IN. EDGE RADIUS

, 2464 2331 • 2-D MODEL 2335°F'.: 0.0

_' 0.4: •

• 'o

•' 0.8

"" 1.2

1.6m

" 2.0 ,._

. i

:T:i • 2.4'2

,!

i 2.8

:_ 3.2.o

" REPORT MDC E1343" FINALREPORT 24JULY1975

EFFECT OF COATING EMISSIVITY ANDALUMINUM STRUCTURE THICKNESS ON

. TIIE RATIO OF 2-D TO I-D MODEL- TPS REQU.I REMENTS

• BODYPOINT1

_. " • TRAJECTORY14414

• R.I. BASELINEHEATINGDISTRIB_

• GAP WIDTH = 0.10" 2-D MODEL

e INNEREDGERADIUS= 0.06"

• MAXIMUMALUMINUM_TEMPERATURE= 350°F '

; COATINGTHICKNESS

_ FLo_.J----_,_ _ _ (%=O.OlSIN.)

, X-HRSI

.,. ,,,,,T:

T; X-HRSI X-HRSI X2-DIXI-DCOATING ALUMINUM I-D 2-D

EMISSI VI TY STRUCTURE MODEL MODEL

" O.80 O.08 2.88 3.32 1.153

0.85 0.10 2.53 2.91 1.150

0.80 0.12 2.38 2.76 1.160

45 FIGURE3Z

' MCDONNELL DOUOLAS Amlr'RORCAUYIC8 CDMPANV. EAST .... i_"

00000001-TSD08

,., ,

IREPORT MDC E1343", FINALREPORT 24JULY1975

::, EFFECT OF COATING THICKNESS

= ON TPS REQUIREMENTS

I BODYPOINT1.... • TRAJECTORY14414

• R.I. BASELINEHEATINGDISTRIBUTION• GAPWIDTH= 0.10 IN.• INNEREDGERADIUS" 0.06"

,, • ,MAXIMUMALUMINUMTEMPERATURE" 3500F

7' •

.... 2-D MODEL -

,. ,.,.,3.4__I__II_I_I_I1I_I_I_i_i_i_I__i_!I_= |]Illll_llllllI1111111111]IlillllllIIItllltll_I_)tllitllIlllitllllllti!il!i!ill!llIlllIiIll!lil!iill

" -" Bl_fl_l,l_EIllI_l_IIiI!"• " " '' " "!}' 3.3 " ' " '" 't t=_ _ lilm_m#__Rm IiIll_iliIIIlll_lillIll_IlllIlllllI_I_l!li,}iillIl= __I_II1111111t_IIlllld{Hili_lll'IiIUIiI!!l!IIll!lllii!ilIiiilti!ilIIi_I_iliililF:iilllil

_" , itiltI!ttItfit_tt_t!tt_If_ttttlIlt_I_ftI_f_ttttt!.tIiittt_I!lttitttttiIt)liiiiUttt!ftttiitt!iitiiillItt_ltttti,4t_I_fittitttJtttit!!t!tiiiittt_titt_!Ltthtilith.tih_lhhlt,,,ftittlfttiitii!ihtrait

_i .oo .oo

• ,,- I COATINGTHiCKNES OF 0.015 INCH ._

_ X2.D HASCOATINGON SURFACEAND GAPWALLS_ '='_"1 l;ji;" 1.16 ithth:,_!-t t tl i_i_iil__!i !'i "u"!ituum,t;,_ ........... ' .... tlIftt llh'!.lh,,l,,,,h,,,l,,,,l,hllm,ll,./]!,,,-,.i;:,,i_ _ _J!Jlt; i_ii !J_!_! _It_

hhtllili h_tl!.ht....It!, h, _,,I,,,! ,.,_,_. ,,_,:lit=_!ii,v...':. !1!11:i"_- " It ' '" ........iIi!........"" ....'..... i_,!"' .... .:;- I_,_,t,,h'_' :'_.... "..................... ,,,, ,......... ,,,ml.... ,,u ......l" _,_..14,..... ,",,,:,...h,,,::..:,.,.,_.:':_ii!ilit!tliilii_l!!,;II_liiliii_

j!t U '_ ;H: °"•. tl_ .,.Iul ! !,ulu:_ iill .... . ,

" _ llllIll_lil(l(!ll|.,.,,lli,,iiiJ!JJiii.,,,h,J,,,'`'=,..._""'"iti!i,,_,,_,_'i_l_!_,llll,,,,,,,,ilII,,i_ , :hl"! I!_: ""Jiii!if! ,:i i'"i!!i!titi ;l_! ...., .,,:.......!Ill_iii :_i.,,:.l:::,.lii:,.:._v__u_I:' IJ_l_i" lh,lll_,ilii!hliilllh"_i"' '_'' .....tiil-: '",< lll,lh,hdiiii,l!!i:.,_,_,,_ .....-.. ,..

I I ' ='" '... Iililii,, lli,i_,_,_,_l!i!ll!i_!!liiUu'"'i_:iil'::::!i_:",,,....iiil_'_,_iJii,,,,:,,:,"_i

'- I I [ .... '._:'.!.:I: '.;::' 1"12'llii'_l!iitih!,llllIlll!llii!""_":_'_u,,._r;_,iiii,_r..,:_,_i ":_"_':'""''"::,' llnilHil _";. ;U; ' '" _:':'l"l_ it i ::;;,,_..,.'_iliillIIIl@iiii!,li;li_i_ _:liu'_ ....="._":"_"""',"',:'. liu....... 1',',; ....

.... ""'"" ......................._!ii,_i_:!l!i!i!!!i!i!i!I!i!iiilll'q'...... "' ,,_....,'",I""I'..........._I_ _:i':it':!..................:iiii" ...._I_'",::_u_:.:,,_:.,,,,:,,:,i,,_ii,,.........,., _.,.,_,...,_:i::iii!i!"::f:ilili_i'_ii':':"

; ' 0 .....Ii:,;) "" 004 .008 .012 .016 .020 .024 ,028

}" |C-COATING.THICKNESS....INCH' T

" tOOi)UC_Bn-,t_0_''l_Z, ;. 46 _'__ pOOI_, FIGURE33

If., I,. MCDONNELL DOUOLAg A_'rI_ONAU'rlCB COMPANY • EAS"r

• _ • ' • _

.......... ? - .................

00000001-TSD09

_EAT I REPORTMDCe_3,a

SHIELDSIZING

FINALREPORT 24JULY1975• i

EFFECT OF GAP WIDTH ONTEMPERATURE OF

ALUMI NUM STRUCTURE

• BODY POINT Ie TRAJECTORY14414• GAPHEATINGDISTRIBUTION

SAMEFOR ALL GAP WIDTHS ....._ • 3.32 IN. HRSI

• O.OGIN. EDGERADIUS

FLOW---_ _ W "_-

-_ f

47 FIGURE34I

M_DONNILL DOUOLAll ASI"ROIIIAUTIC_I 4_OMPAitlV. MAlT

............" +.......... .......... " - " " +;::._ +.+z_+

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: _EAT _HIELOSIZING

-- _ J REPORT MDC E1343FINALREPORT 24JULY1975

GAP WIDTH EFFECT ONTPS REQUIREMENTS

• BODYPOINT1• TRAJECTORY14414

• MAXIMUMALUMINUMTEMPERATURE= 350°F ..................

_-" • MDAC CORRELATION,EQ. 4-17

b_

: I1 ,.COATINGTHICKNESS

(% O.OlSIN.)i I FLOW_ _ W_'--

:! i_ _ _tl .....

I, li, • _ ................ I....................... J....ih;.;i'H ....:: ;,: :"; :::. :::: ";::

:{i , _<::i?_]_!i_i_!_!_!!_!_!_i_i!_i;_:_i!!_!iii_i!i_:_::_:_!_::!::_!i_!_!::_F:T_;_i:_i;:i!I:ill

: _ _ I_;_I_,_i_li:iil_iiil_i_li!_Ii_!iI_%_iI_!_ _i_> i_ _.4_-!_L_IIi!l!ii_iiii_iiii_!illii!lii!;i_il!iiliiii,_iliii_!;:ii_!iii

i E_ - INNEREDGE_i!!'!i_: .: .._:..!i{_ti:Tii!iil!ii ....,_:i!ii!,::i_ _£_ "

, I " RADIUS- IN_iiit_ _ ]_ ii _ :::::.:.!::, ::::]ili::

.....'....... " ' '"" -:.:._t_i!.l:;_:._.:....1_-:i.:.:i:il: _i_ i:: ii_:iii!il_ii! "

11 .....,:;:::_,:;_:;::__:':-:l "-H 'F- :::": _'::: ::_- ' _:I:.: _. _i: ii::!_::l_!!!l_::!.!::.l,,'_i:::::;:I:_.,L:i_n,;::i'I':_:!!:._!l:!:!!_::i_i_l;_/_:_ 'I.:: _ii:l__::_I::-;;_:;__-":.:I': ::.::K::;T;!:;:_:_:;:,T-:.::_ ,,}-., _ 0 .04 .08 .12 .16 .20 .24 i

:., W - GAP WIDTH - INCH '

ii:. ill _

i:,:. 49 FIGURE36 _.,

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_" _EAT SHIELDSIZING I REPORT MDC EI,'143-°:_. FINALREPORT 24J_L,YIo7_

: .... INCREASING EDGE RADIUS REDUCES TPS REQUIREMENTSR,I, BASELINE HEATING DISTRIBUTION

1.30

._ _ z'_' " NEARNOSE.; : _ 1.20

*,._ _., BODYMIDPOINT:. .. _ AFT FUSELAGE"

,.n , 1.10i_=.

1.00

. 0.0 0.04 0.08 0.12

Ei - INNEREDGERADIUS- INCHES

50 FIGURE37

-. MCDONNELL DOUGLAS ASTRONAUTICS COMPANV. £A,$T

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:, REPORTMDCE1343.. FINAL REPORT 24JULY 1975T

.u

EDGE RADIUS EFFECT ONTPS REQUIREMENTS

.. • BODY POINT1 -

:_ • TRAJECTORY14414

" • MAXIMUMALUMINUMTEMPERATURE= 350°F

;:i_ • MDAC EQ. 4-17 HEATINGDISTRIBUTION

• ..

:;:_ COATINGTHICKNESS

FLO,,a wF.--F" c=o..olsIN.)

?r I C.,..t

i 1_ i "

=...... ,... p :,;:.::::::..:.:..:::,'...;::--MDAC CORRELATION,EQ.4-17

iiiiI_iWIDTH-INIi:::::!i_i_:_iii..li_ii_]ill (C. SCOTT DATA- JSC lO MW)• i;i_::::;':i::i_':....:::::'':n:::::'::"_'.:: 'i_

!:" _"_:l:!'i_:;:l:.'::JO.20::_r:;'-':':.:.:l.::..;-'I:I_.!;I:_H_---- J,, MA_S_RF/R.I, CURVE

i:il _U_L;..i_-__I!!:::!!_i_i'_.__ilUi'..(C. SCOTT DATA- JSC I0 MW)i::; 1.4 _L!iiii!!!i _L:!::i ;: i]iiii__ (_ DERIVEDFROMTESTDATAi% [.I_i_F_'!!_!iliIi!'.T:,']_iiiiiiiti_!l!iiY_ OBTAINEDFROMNVlES'20

:= _l_____--_iiiiJiiiilili__LENT DUCTFACILITY,_i?i_!,:_: _ T_H_-_I_I)_-r:-._!__E F. MDCE1248 :.'---.!!!iliU!F...!i:_iii, !,:_:_L_::I:_:I :._lii!lii_,.,..,: t .._ .,..:r

• _..I_=t:._ -_:..<-................... ,'_,_',............_ _,_'_l_,J;"_i;"-':_:_-_ ....J"'1 3 ........... :_':: :: ::::'"::.-..' '-' : :' : ' '=:::::::fl'il..._!j' : " _.... :_::':::"::• :::..:::....:.:::....:............................. :................. ....I.,!:L,.,t:-_..:...:.._-:...

::::::"!':1 ,", " '.. ..: ........ ::.,._:::...:., ....... !,, ."_ ! _ - •'. .... ...... ,,,,., .,,,,_.................,,....:._:_..r...!_i:_'r"_2"".:'- •:::::_::]:_: '' ,,U_ _.;.......... I ,_._;"' :J I il1: .... • ' ! ' ' : :' :. "' :.: ...... :-, ...... , ,. , , • .._'_7... *...

I"'*

:_ ........... "'"_ ........................ _.... ; .... : ' _'_" _ 1 " ':k ....... .............. ......... ...............:'r"-*................::: ""_ _:.°7:............. _ : ;I": _ ....::GAP WIDTH ,=.• : ': .'::::: "'"'_..............'

-- l 2 _ = .10 IN. -_!li_ifl:!/,_::;;l_l;_"_ N •

_:::: :':: ::::: .10 .... ::,_:: ..... "".'......... -• .,'T'_'...'_::°.'*_.. : .... :: .............. : ,

, , ; ; ' ::Y: :: ; ;::: :::: ::: .:' ,,;..h .............. I ......i i!iiiiiiiiiiiiiiiiiiiiii14 ..L; ........... 1' _ ........................• '" "".....•'| ' ' . " .: . , ..... I...... ,, . .I • •

_,." I.I'r-".... "- "........... " ....i ® DERIVEDFROMTESTDATA :l__:___ii:t OBTAINEDFROMAMES 20 MW I,J.__'.__ _GAPWIbtH ='"

" _i TURBULENTDUCT FACILITY, _q_::. 10 IN.Illl/ I 4_v4 _ ' " I ' _" ' ' I le I ' I I' II I I I 14• .. : l:]il:: :,i: : : : . , i ;,, • |

' 1 ':'it!;.'i!l:,':,.:.;l.::.!.. I I,,,.l.. I..1 .... !.-_ .....ili::i1: .,,:=:, ...... UUlU:' . T

fi_ 0 ..04 .08 .12 .16 .20 .24 .2B !, ;,

I."_', El - INNEREDGE RADIUS- INCHES ii.'3

:.... FIGURE40 :_,;,i: 53

'= _ MCDONNELL DOUGLA_ A._TRONAUTIC_ COMPANV * EAs"r

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I .II II II ' H I m II i

'" ATSHIELDSIZINGREPORT MDC E1343

' FINAL REPORT 24 JULY 1975

IHFLUENCE OF GAP WIDTH Oil

'-- HEATING Ill TRAflSVERSE GAPS

_ O, 157 C[I EDGE RADI US ..........

" - • N,IES20 _! 2-x 9 INCHTURBULENTFLO&JDUCT FACILITY

?

':') 1.2

p

• L

• J.

0,8 :_t .."zr'h-,,

:- "If:I!,

-_"L

0.6 ;i_:

- _ ::II ill:

0.4= iUi

; _ ]i!- :2 0"

4,I,

_ _ 0.2 l_:il_ .... iili

0.0

_,) -0.2

0.0 0.2 0.4 0.6 0.8 1.0 1.2 1.4

) ': Z - DISTNICEFROMSURFACE- cm

,'_ 55 FIGURE42

, J

MCDONNELL DOUGLAS ASTRONAUTICI COMPANV . EARIP

00000001-TSE04

.... "- REPORT MDC E1343.... .. FINALREPORT 24JULY1975

!-.... EFFECT OF TRANSVERSE GAP HEATINGi ON TPS REQUIREMENTS.. (BODYPOINT 1) ..

.... - EDGERADIUS GAPWIDTH X-HRSI X2-D/x1.D(IN) (IN) (IN)

i l-O MODEL- NOGAP 2,88 -!- • ,06 .05 3,57 ........... 1,25! : * .12 .05 ........ 3.44 1.19i___ .25 .05 3.22 1.12

i :: ,06 .10 3,82 1.33[

i - ,12 ,10 3.65 1,27i_ ,25 .10 ............ 3.42 1.19

! ,06 .20 4.10 1,42! '" .12 .20 3.92 1,36

" .25 ,20 3;72 1,30

THEABOVERESULTSBASEDONEQUATION4-17,i . N

.... m,mmmmmnlmi

i_ IALUMINuM_" " _COATINGZ X-HRSl X-RSI X2-D/ X3-D/ ........_

i I (IN) (IN) I-D 2-D XI-D X1-0(IN) (IN) ........,,i i i , i

" J_, .015 2.88 3,32 1.15 1.30i _ .015 2.38 2.76 1.16 --Z ,

i ,08 ,00"-"'5 2,88 3,25 1,13 --i .... ,08 ,015 2,88 3,32 1,15 --

- .08 .025 2.88 4.61 1.60 --m

!

HEATLoAD X-HRSI THICKNESSRATIO• 2-0._, (IN)i'

..... ] ,0 3.32 1,01.2 3.36 1.01

: 1.82 3.84 1.16,_;- I. 963 4.34 I. 31 ..,

..__ 1) R.I. Baseltne Heating

......... 2) 0.10 inch gap

: ,-,, 3) 0.06 Inch inneredge-radius

_. 57 FIGURE44

" _?"" MCDONNELL DOUGLAS AS'rRONAUlr'Icf_I COMPANV. lAB'#"

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"_ _EAT SHIELOSlZlli6 IREPORTMDC E1343

..... FINAL REPORT 24 JUI.Y 1975

- APPENDIX A PRIORITY CASE LIST

_ .. Seventy-two priority cases were run. A llsC describing the contents of each,*._• case, thickness of HRSI used, the associated temperatures and the required thick-L=-- .t"

_, nesses to restrict the aluminum temperature Co a peak of 350°F has been prepared.

The baseline configuration being considered for the TPS is listed after priority -

;:: Case 7• The majority of chase cases consisted of two or more computer runs to

: reach .the required thickness, totaling approximately 145 computer runs.

The HESI thickness for some of the computer runs has been flagged wlth double

:- asterisks. The thermal model used for these runs ned some irregularities end was

.-_. later revised to be more realistic• The thicknesses and temperatures.assoclated

with these runs should not be used. as absolute values alone, but can be used toY

i' show sensitivities, i.e. varying gap heating distribution (priority cases .2, 3,

4, 5, and 5-1)

! •

i.:!

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,',i° MCDORINE'LL DOUGLAS AIITRONAIJTI@II COMPANV * lAB?

I _ ............... =i

- O0000001-TSE07

EATSHIELDSIZlHB J REPORTMDCE1343FINALREPORT 24JULY1975

t ..... " ....................

PRIO,XTV X-HRSXT )AL X-HRSl: CASE# CONTENTS (INCHES) OF @350°F

(INCHES)1 B.P.3 (1157),one dimensionalmodel,coat- 1.50 261 I-T

tng emissivity - 0.8, aluminumt = 0.08 tnch 1.00 333 0.910.50 483

2 B.P. 3, two dimensional model, basellne 1.50"* 276

configuration* 1.02"* 348 II'Ol**1.00"* 3520.98 350 0.98

3 B.P. 3, baseline configuration except that 1.20"* 312 0.99**smoothwall heating (qp_p/qSURFAr_= l.O) 1.00"* 347is assumedto verttcal-(angency"_Btnt ofradius and zero heating below tangency point

4 B.P. 3, baseline configuration except that 1.O0** 345smoothwall heating ts assumedto vertical 0.96** 353 0.975"*

• tangency point of radius.and the gap is 0.90"* 366 .closed to prevent radiation transfer in the 1.00 346 0.98gap

5 B.P. 3, baseline configuration except the 1.50"* 275 1.0"*coating terminated 0.5tnch from bottom of 1.00"* 351the gap

5-1 B.P. 3, baseline configuration except the 1.02"* 343 0.985**coating is removedto the vertical tangencypoint in the gap

6 B.P. 1 (I040), one dlmenslonal model, coat- 3.50 297tng emissivity = 0.8, aluminumt = 0.08 inch 3.00 338 2.88 ,,

2.50 393 I

7 B.P. 1, two dimensional model, baseline 4,5"* 293 Iconfiguration 3.6** 350 3.6**3.5** 3583.20 360 3.323.32 350

*Baseline configuration: 1. Heating distribution in gap (R.I. Baseline)2. Hodel width = 3.0 IN.3. Inner edge radius (El) = 0.06 IN.4. Gapwidth (W) = 0.10 IN5. Coating emissivity (c) = 0.806. Coating thickness (_c) = 0.015 IN.7. Alumtnumstructure (t) = 0.08 IN.8. SIP + RTVadhesive = 0.175 IN.

**Initialthermalmodel and assumptions.

A2

• M_DONNELL DOUGLAS ASTRONAUTIC8 COMPANV. EABT

............................._.... i _1 .......:_I__ii_-'_:_'_':_r'_ _:_" -_ "_ __- _;,;-_..........."_

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REPORTMDCE1343

: i !!! iiiiiiiiii!i" FINAL REPORT 24 JULY t975

PRIORIT X-HRSI: CASE# CONTENTS (INCHES) 'I4AX)AL!@350OF

8 B.P. 1, baseltne configuration except that 3.32 343 3.23 ismoothwall heating (q/q = 1.0) is assumed 3.24 349

: vertical tangency point of radius and zeroheating below tangency point

" 9 B.P. I, basellne configuration except that 2.95 359 3.04• smoothwall heating ts assumedto verttcal 3,04 350

tangency point of radius and the gap fs:_: closed to prevent radiation transfer fn the ........... gap

i-_, 10 B.P. 1. baseltne configuration except the 3.32 346 3.27 _i coating terminated 0.5 tnch from bottom of 3.27. 350

the gap

11 B.P. I, baseltne configuration except 4.5** 345F model width = 1.5 inches............... 4.4** 352 4.43** t," 3.6** 411

; 12 B.P. I, baseline configuration except model 3.6** 334 3.49*** wtdth- 4.0 tnches: t

'_::: 13 B.P. 3, basellne configuration except model 1.02"* 368 1.1"*i width = 1.5 inches !

! ,. !ii

}, 14 B.P. 1, baseline configuration excePt inner 3.80 327 3.49 1! : edge radtus = 0.001 inch 3.50 349

""-, 15 B.P. 1, baseline configuration except tnner 3.50 343 3.41....: edge radius = 0.03 tnch 3.41 350

_ 16 B.P. I, baseline conflguration except inner 3.00 372 3.24 .--_ edge radt us = 0.09 I rich 3.26 349 ,,

. i_. 17 B.P. 1, baseline configuration except inner 2.85 381 3.17 ,_t edge radt us = 0.12 tnch 3.20 349 ;

li 18 B.P. 1, baseltne conf4guratton except no 3.60** 349 '

'_il lateral conduction tn SIP at gap _,: _ 19 B.P. 1, baseltne configuration except no 3.60** 347

! conduction through SIP at gap

20 B.P. 1, baseline configuration except coat- 3.50** 326 13.16"*: I_ tng emissivity = 0.85, alumtnumt: = 0.10 3.20** 347

tnch 2.91

I A3

':_ : MCDONItlELL I_OKIGJLAS A_I'rRONAUII'ICll _OMPANV . lAST!..

O0000001-TSE09

fREPORT MDC E1343

FINALREPORT.__ 24 JULY 1975

_/ ! Im

j ,RIORZ ' X-HRSIT,Ax X-,RSICONTENTS (Z,CHES) 350OF

(INCHES)

21 B.P. I, baseline configuration except 3.50** 315 3.00**alumtnumt = 0.12 tnch 3.00"* 350

2.76

22 B.P. l, one dimensional model, coating 3.50 272emissivity : 0.85, aluminumt - 0.10 tnch 2.50 352 2 53

2.00 420 _ ....w

22' B.P. 1, one dimensional model, coating 2.50 _dlemissivity - 0.85, aluminum t = 0.08 inch 2.00 45_ ..... _..77

23 B.P. 1, one dimensional model coating 3.50 264emissivity- 0.80, aluminum t :...(1.12.Inch. 3.00 295

2.50 338 2.382.00 400

24 B.P. 3, baseline configuration except inner 1.00 350 1.00edge radtus - 0.001 tnch .... i

__ 25- B.P. 2 (1077), basellne configuration except 2.20 350 2.20Inneredge radt us = 0.001 Inch

25A B.P. 2, one dimensional model, coattng 2.50 286emissivity = 0.80, alumtnumt 0.08 tnch 2.00 338 1.901.50 , 418

["

26 B.P. 2, baseltne configuration 2.22 .334 2.122.10 352

27 .P. 2, baseline configuration except inner 2.08 345 2.04dge radtus= O.12 tnch

28 3.P. 3, basellne configuration 1.01 344 0.98 :0.98 350

29 _.P. 3, baseline configuration except inner 0.97 347 0;96 Iiadge radius = 0.12 inch

30 B.P. I, three dimensional model, baseline 3.75 349 3.74 i:onft guratlon _:

31 B.P. 1, baseline configuration except gap 3.32 344 3.24width : 0.05 tnch

A4

MCDONNELL DOUGLAS AJ'I'RONAU'r|t_II COMPANV . RAIl"L

OOOOOO01-TSE10

_ SILICAHEATSHIELDS|ZlN6

.; f_ _ FINALREPORTI R_P°RTMDce_3'3_`JuLY,,TsI1_ '

PR,oRIT X-HRSX) H-'.".-.'CASE# ..... CONTENTS INCHES) AL 3=O,,F

32 B.P. 1, baseltne configuration except gap 3.32 353 3.36 iwidth = 0.15 tnch

• 33 B.P. 1, I}asellne configuration except gap 3.32 355 3.38wldth = 0.20 Inch

34 B.P.1, Baseline configuration ustng method2 3.32 353.5 3.36nearing distribution (C...Scott, JSC, .Tables) 3.36 350.4

35 B.P.1, Baseline configuration using method 3 3.32 392.6 3.84heating dtsttrubtton (MDACcorrelation of 3,86 348.8

: ScottData,EQ. 4-12)

36 B.P.1, Baseline configuration using method 3, 3.32 426.8 4.34' distribution (MDACCorrelation Scott data,,_ EQ. 4-12)

..: 37 -, B:P.I, Baseline configuration using method 3.32 694.0 "- ,_ 3AAheatingdistribution(MDACcorrelation "

• _ of Scott data, EQ. 4-12)

,: _, 38 B:P.1, Baseline configuration using metl_od1 3.32 389.9, heating distribution (R.I. baseline, Scott 3.70 361.1 3.88

!:. data),gap width = 0.20" 3.88 349.4I:

i:. 39 B.P.1, Baseline configuration using method 3 3.84 348.9 3.82i (EQ. 4-17) heating distribution (M-3, 3.82 350.2

"_ i is MDACcorrelation using 0.062" as edgeradiusfor sharp cornerdata),gap width =

: Ii_. I! 0.10", inner edge radius = 0.06"

.. 40 B.P.I,Baselineconfigurationusingmethod3 3.88 365.1 4.10 _EQ. 4-17 heatingdistribution,gap width . 4.10 349.7 :,_

I 0.20" inneredge radius 0.06"

t," R 41 B_P.1, Baseline configuration using

Method 3 3.88 339.8 3.73• _ _. 4-17 heating distribution, gap width = 3.72 350.9 _

:' _ 0.20",inneredge radius= 0.25" !!

_ 42 B.P.1 Baseline configuration using method 3 3.88 353.0 3.92 }_- _! EQ. 4"17 heatingdistribution,gap width = 3.92 350.3 ,j:.. !i 0.20",inneredge radius= 0.12-"

• _ 43 B.P.I,Baselineconfigurationusingmethod3 3.84 336.5i;_ EQ. 4-17 neatingdistribution,gap width = 3.60 353.9 3.65 ,; 0.I0" inneredge radius= 0.12" 3.65 350.0

!i: ', MCDONNELL •DOUOLA8 AmTIIPONAUTICI COMPANY * IRA • • ,_

0000000-TSE

: ATSHIELDSlZill6

FIHAL REPORT REPORTMDCel:l,t22,( JULY 1975

", _...... , i | I -- ,s t ._

X-HRSIPRIORITY -HRSI TMA_AL @ 360°F

- CASE# CONTENTS INCHES) (OF) I(ZNCHES)

":_. 44 B.P.1, Basellne conftgural_ton ustng method 3 3.73 .....:327.5 3.42 jEq. 4-17 neattng dtstHbution, _ap width- 3.46 347.00.10", inner edge radtus" 0.25'

45 FLAP(B.P.2.12), one dimensional model, coat- 3.00 330.9tng emissivity = 0.8, alumtnumt-O.08". 2.55 377.1 2.80 .........

.... 2.00 460.1.

46 FLAP, Baseltne conflguraUon ustng method 3 3.62 358.5 3.74' EQ. 4-17 heatlng distribution. 3.75 348.8

- 47 FLAP, Baseflne configuration ustng method2 3,62 325.4 3.27.... neattng distribution. 3.2g 348;4

-- 48 FLAP, Baseltne configuration using method 1 3.62 319.4• .: heattng dlstHbutton. 3.23 347.9 3.20..... 3.20 350.4

-" 49 I8.p. 1, Baseltne configuration using method 3.32 344.6 3.25"1 neatlng distribution (R.I. baseline, 3,24 351.2

"' " _ II:- Scott data), coattng thickness = 0._)05. : ....

_ 50 B.P. 1, Basellne configuration using method 3.32 351.3 3.34I1 heating distribution, coating thickness = 3.34 349.8

::: I0.035".I

_ 51 IB.P. 1, Basellne configuration using method 3.32 346.6 3.29,.. 1 heating distribution, coating thickness = 3.29 349.0"" O.010".

: 62 Flap, one dimensional model, tntttal T=gO°F 3.00 307.3coattng emissivity _"0.85, aluminum 2.80 325.6 2.57 ...............t = 0.081". 2.55 352.1

53 B.P.1, 3-D Model, baseltne configuration 3.75 418.1using method 3 Eq. 4-17 heaUng.dh-.

i_ tributton.

54 Flap, 2-D medal, only external surface 2.55 364.1 2.68neattng, gap ann radius heating = 0.0, Gap 2.67 350.9 i

• wldtn = 0.10", inner edge radius - 0.001", ,_. aluminum= 0.081", coating emissivity

= 0.85, Initlaltemperature= 90OF i

55 Flap,3-Dmodel, other data In P.C. #54 2.55 374.2 2.78.... 2.78 350.0

o,

.....• A6

"" MCDONNELL DOUGLAm A-q?RONALITIC_-I COMPANV ,rEA|7

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I REPORTMOCel,_4__'_, FINALREPORT 24JULYi'..

i! ....!i PRIORITY X-HRSI TMAX)AL X-HRSI:_ CASE# CONTENTS INCHES) (OF) @350°F: _,! (INCHES) ......

_ 56 B.P.1, Baseline configuration using method 2.88 389.9_! 1 nearing distribution (R.I. testof HRSI 3.32 348.1 3.30t tiles, task 28, Ref, MDACTTN NO. E242-76) 3.30 349.9t_

!i in-line gap.

i 57 B.P.2, Baseline configuration using method 1.90 376.8 Z.11"L 1 task 28 heating distribution, in-ltne 2.12 348.9

!: gap

;_ 58 B.P.1, Baseltne configuration using method 3.63 346.6 3.59i 3-.Eq 4-17 neattn9 distribution, gap width 3.57 351.3p_ •

l = 0.05", inner edge radius = 0.06".

_J 59 B.P.1, Baseltne configuration using method 3.46 349.0 3.44i_, 3 Eq. 4-17 nearing distribution, gap width

= 0.05",inneredge radius= 0.12"

_! bO B.P.I,Baselineconfigurationusingmethod 3.22 351.0 3.23 _ ._i 3 Eq. 4-17 heating distribution, gap, ...................._wldth- 0,05'!,inneredge radius= 0.25" _

_i 61 B.P.I, Baseline configuration using gap 3.32 350T7 3.33!,>

heating distribution by O. Marssdorf of ...... 3.33 349.9R.I. (C. Scott Dataqrans. Gap) gap width_ = 0.I0",inneredge radius= 0.06"

li 62 B.P.I,Baselineconfigurationusinggap 3.33 355.1 3.39

_ neatingdistributionby J. Harssdorfof R.I. 3.39 350.2(C. Scottdata - Trans.gap) gap width =

_ 0.10",inneredge radius= 0.125"

il 63 B.P.I,Baselineconfigurationusinggap 3.33 372.8 3.60nearingdistributionby J. Marssdorfof R.I. 3.67 344.7(C. Scottdata - Trans.gap) gap width = 3.60 350.2

I O.lO",inneredge radius= 0.25"64 B.P.I,Baselineconfigurationusinggap 3.3? 338.2 3.18

nearingdistributionby J. Marssdorfof R.I. 3.1(J 351.4(Curvelabeled8/14, a revisionof R.I.Baseline)gap width = O.lO",inneredgeradius= 0.06"

iA7

i'" _i MCDONNELL DOUOLA_I ASTRONAUTICS COMPANY. KABT

1,,_ ..... "_-r-"" ........ ." ? " --J .... = ...... . -:i.._ -_-_ : _--- _ __ ....

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--"................. 1

I

' P|IOR ITY' CONTENTS (-HRS[ X-HRSI

_" L-_CASE# [INCHES)TMAX)AL(oF) @350°F

.: ............. (INCHES)

_ 65 B.P.I;....('Qr=18700 BTU/FT2) one dlmensional2.547 353.3

model using Inltlaltemperaturedistribution iSIP properties'andthicknessof R.I.,coatingemissivity= 0.80,aluminumt = 0.10

65A t__J,as 65, exceptcoatingemissivity= 0.85 2.547 343.9

6SB Qe = 19115 (approx.BP 2110, Qe = 19117), 2.547 347.0one dimensionalmodel using Initlaltempera- " --

_" • ture distribution,SiP propertiesand _.thicknessof R.I.,coatingemissivity- 0.85.aluminumt = 0.10"

67 B.P.1, Baselineconfigurationusing heating 3.4b 321.7distribution from AmesTurb Duct Tests. 3.06 354.7 3.12Ref. MDCE1248 Pg. 226, Inner Edge Radius 3.12 349.3

..... = 0.25"

6b B.P.I,BaselineConfigurationusing Heating 3.32 370.3 --"distributionfromAmes Turb Duct Tests, 3.82 334.3 3.59inneredge radius= 0.06" 3.70 342.3

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__ _ .... APPENDIX B TEHPERATURE-TZMEPLOTS

The priority cases for which data have be_,_ I_lotted are: 7,8,9,10,14,17,30,38,

39,40,41,42,43;_4,46,47 and 48. For the conter, ts of the plotted cases refer to

- "......the preceed£ns Appendix. The temperature-time data for the unplotted cases are.

recorded in the form of computer tabulated output. This has been sent to Mr .............

H. 'K. Larson of NASA Ames.

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,_ APPENDIX C THERMALPROPERTIES

• _ . Thermal properties were used in the analysls as provided by NASA-A._s from

Rockwell International Corporation, except that those for the RTV bond and strain

: isolation pad. Composite thermal properties were used for the bond/SIP/bond layer.

--- Interpolation with pressure in the property tables was logarithmlc. _,- ,

The properties used in this analysis are listed in the tables below.

. H SI COATING(SZL COSCA ZDE"=., .... Density - 104 lb/ft 3 Emittance - 0.80

: Temperature Conductivity Specific Heat°F BTU/ft-hr-OF BTU/LB-°F

- -250 .425 .15

-150 * .450 .17_ 0 .487 .19

250 .550 .215

= 500 .604 .24! 750 .654 .26i:_ 1000 .704 .285

i_!i' 1250 .750 .30" !500 .796 .315 "

1700 .829 .325 ......

1750 .837 .33

1950 .871 _ .342000 .883 .345

_ 2100 .896 .35

_: 2150 .904 .353-! 2300 ,933 .36 |JL

HIGH TEMPERATURE REUSABLE SURFACE INSULATION (HRSI)

,=, Density = 9.0 Ib/ft 3

,r _ Pressur( Conductivity - Btu/ft-hr-°F

_"i_ Temperaturt_,.._ 0o21 2.12 21.16 211.6 2116. I

• -250. 0.0050 0.0075 0.0150 0,0216 0.0233 i_- O. 0.0075 0.0100 0.0183 0.0250 0.0275 !_ 250, 0.0092 0.0125 0.0225 0.0316 0.0341:L/:_ 500. 0.0125 0.0167 0.0276 0.0400 0.0433_ _50. 0.O175 0.021_ 0.0325 0.0492 0.0534 _" I000. 0.0233 0.0275 0.0392 0.0600 0.0658

!_; 1250. 0.0308 0.0350 0.0492 0.0725 0.07821500. 0.0416 0.0459 0.0617 0.0875 0.0942 i

/_* i 1750. 0.0567 0.0610 0.0767 0.1060 0.1130

i_': i 2000. 0.0734 0.0782 0.0942 0.1270 0.1360

-. 2300. 0.0966 0.1020 0.1160 0.1550 0.1670 /'

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HRSI PROPERTIESCONTINUED

Temperature 8pocific Ileal:°F B_u/Ib.°F

-250. 0.070

-150. O. 105O. 0.150,

" 250. 0.210500. O. 252750, 0,275

1000. O. 2881250. O. 2961500. O. 3001700. O. 3O21750. O. 3032300. 0.303

s.TvBo.D_D .O_XFELT.(SZP)CO_,OSZT_.Densil:y - 12.28 lblfl:3 Specific Heat - 0.29 Bl:u/lb-°F

Temperal:ure Conducl:ivil:y..... oF Btu/fl:-hr.°F

I 40 ...... 0.0182400 0.0227540 0.0301600 0.0380

2024-T8XX ALUMINUM

Densil:y - 175 Ib/ft 3

Temperature Specific Heal: Conductivity A. oF Btu/Ib-°F Btu/ft-hr-°F ,

; -400 0.088 --

' -300 O. 117 ---200 O. 147 69,6

0 O.195 84.0

200 0.216 95.0300 0.224 99,0

' 400 0.233 102.5

600 O. 250 104.5

_ C2t

MCDONNE"(.L DOLIGL4S A._JTROFWAUT'ICS COIMIPAItlV . £AS'r

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000(_0(3£_4-T.q R i 9