Adp Final Aravind

8/17/2019 Adp Final Aravind

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DESIGN OF 100 SEATER PASSENGER

AIRCRAFT


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REASON FOR CHOOSING

AROUND 46% OF INDIA’S ULTRA HIGH-NET-WORTH INDIVIDUALS LIVE INSMALL CITIES, MOST OF WHICH ARE STARVED FOR FLIGHT OPTIONS.

BUT RUNNING DAILY AIRBUS A32 OR BOEING !3! FLIGHTS TO AND FROM THESE CITIES IS NOT PROFITTABLE PROPOSITION.

T"# $&'#& ()*+# D&. A. P. . A/+01 1' ") 11#+ $& +#5#1('# $ )##& 7# *&&$ * "# 0&8. I $0* &9*:#+ /8 HAL


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INTERESTINGLY, INDIA;S TRANSPORT AIRCRAFT DREAM WAS INITIALLY CALLE

THE NATIONAL AEROSPACE LABORATORIES


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MISSION PROFILE


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DESCRIPTION

Phase 1 : Engine start and warm up

Phase 2 : Taxiing

Phase 3 : Take !

Phase " : C#im$ t %ruise a#titude and a%%e#erate t %ruiseSpeed

Phase & : Cruise

Phase ' : (iter

Phase ) : Des%ent

Phase * : (anding

Phase + : Taxiing

Phase 1,: Engine shut dwn


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A*&&$ +#)*9 /# /&# *"# '7& (")#)

CONCEPT-.( DESI/N:PRE(I0IN.R DESI/N:

DET.I( DESI/N:


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COLLECTION OF SIMILAR AIRCRAFTSDATA


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PERFORMANCE GRAPH

6 ! !

2

3

4

6

!

&0*)# )(##+


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6 ! !

2

4

6

2

4&0*)# )(##+ VS )#)

&0*)# )(##+ '("

)#)

6 ! !

2

3

4

6

!&0*)# )(##+ '(" VS #*9" W


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6 ! !

2

2

3

3

4

&0*)# )(##+


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WEIGHT ESTIMATION

To estimate the following parameters of or !on!eptal "esign

Gross #ta$e %off weight &'T0(

Empt) weight &'0(

*ission fel weight &'F(


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Phase +,-. /oiter


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10)*

&1,*1 kg

e2)*3+ kg

413)+2 kg

p+,,, kg

%"&, kg

Range",,, km


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AIRFOIL SELECTION


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AIRFOIL SELECTION

NACA AIRFOIL FOR ROOT - 23

NACA AIRFOIL FOR TIP - 232

FROM SURVEY, RANGE FOR CL ' IS BETWEEN .2 TO .

CL '


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WING LOADINGJ K !4!.4!


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LANDING PERFORMANCE


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1+*9 +*)#

R V$ 2.29

R 4.6 '

"$ R


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S9 R S*

S9 2.4 '

FROM SURVEY, THE LANDING DISTANCE

3! '

S S S9 S$

S9 S- S- S$

GROUND ROLL DISTANCE


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WS &*

N


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TAE OFF PERFORMANCE


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T# +*)#

S9

0+234#&T#'(

FRO* S5R6E78 TA9E OFF DISTANCE

: 1400 m

R Sin ;


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R 3.2 '

5STALL

VSTALL !.43 ')


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C)- J-


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3.


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POWER RE?UIRED

POWER RE?UIRED PR T VQ

!6.4 W

.4 Q-.6

FROM SURVEY,


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EN/INE SE(ECTION

pratt5whittne6 P',,,T6pe: Tw sp# high $6passrati Tur$4an

(ength: 1,* in 829)" m

Diameter: &'9& in 819"" m

Dr6 weight: &,"' #$s 822*+ kg

Cmpnents

Cmpressr: sing#e stage 4an; " stage#w pressure %mpressr; ' stage highpressure %mpressr

Cm$ustrs: .nnu#ar

Tur$ine: sing#e stage high pressure

tur$ine; 3 stage #w pressure tur$inePer4rman%e

Thrust: 22;1,, < 2";,,, #$4 8++ < 12& kN

O=era## pressure rati: 2'91 < 2*92

>6pass rati: "9* < &9,

Thrust


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POWER LOADING

PA 624 W

POWER LOADING


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*9 )(#**

4D

W"#, CD


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CENTRE OF GRAVITY

CO0PONENTS EI/?T8kg

'@ $4 19+2 m 4 9

12@ $4 39*" m '* 1+*9 9#& % W 3!2. 9

2&@ $4 * m (81+ /8 4 9

3)@ $4 119*" m #+ #0*('# 4 % W 4.6 9

"&@ $4 1"9" m

$0)#19# #*9" '*

1+*9 9#&

3% W 6.! 9

',@ $4 1+92 m (81+ /8 2 4 9

+3@ $4 2+9)' m

"&*:1 5#&*1

)/*1*:#&

3 % W 6.! 9


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FRO* T


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SUMMARY OF THE REPORT


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In the pro!ess of estimating these performan!es parameters8 we ha?e fon" other

!hara!teristi!s of or airplane.

a2 Ta$eoff gross weight 'TO +1041 $g

=2 Fel weight 'f 1@3> $g

!2 Empt) weight 'e >@43 $g

"2 'ing loa"ing +@0 N#m>

e2 'ing areaS 312- m>

f2 *aimm lift !oeffi!ient 12@

g2 /#D ma 1+

h2 Aspe!t Ratio AR +2@>3

i2 TR,ma 11+ 9N &Tr=ofan engine(

2 Engine sele!te" &P' -000 (

Adp Final Aravind

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