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R

OVERALL WEIGHT OF THE MODEL Wo 1200

11.772

STALLING SPEED Vstall 40

11.11111111

SERVICE CEILING h 500

TEMPERATURE AT SERVICE CEILING T 284.75

DENSITY AT SERVICE CEILING 1.167202682

DINAMIC VISCOSITY AT SERVICE CEILING 1.77293E-05

(CL) max OF THE AIRFOIL 1

WING LOADING W/S 72.049548267.344500333

WING AREA S 0.163387562

ASPECT RATIO AR 16

WING SPAN b 1.616849091

TAPPER RATIO Ct/Cr 1

ROOT CHORD LENGTH Cr 0.101053068

TIP CHORD LENGTH Ct 0.101053068

MEAN AERODYNAMIC CHORD c 0.101053068

LENGTH OF FUSELAGE Lf 1.032036849

HORIZONTAL & VERTICAL T

HORIZONTAL DISTANCE B/W CG & AC OF HT 70

HORIZONTAL DISTANCE B/W CG & AC OF VT 60

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SHT 0.011793439

ASPECT RATIO OF HORIZONTAL TAIL 8

SPAN LENGTH OF HORIZONTAL TAIL 30.71603992

CHORD LENGTH OF HORIZONTAL TAIL 3.83950499

SVT 0.008805768

ASPECT RATIO OF VERTICAL TAIL 2

SPAN LENGTH OF VERTICAL TAIL 13.270846

CHORD LENGTH OF VERTICAL TAIL 6.635423001

AERODYNAMICCRUISING VELOCITY 45

12.5

REQUIRED CL VALUE OF THE WING 0.790123457

SPAN EFFICIENCY FOR THE WING 0.8

REYNOLDS NUMBER 83160.03381

CO EFFICIENT OF FRICTION 0.004605118

Swet/Sref 4

CD,0 0.018420471

(L/D )max 17.72

K 0.043222694

COEFFICIENT OF DRAG 0.045404187

DRAG 0.676474138

POWER REQUIRED 8.45592673

0.011335022

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C PLANE DESIGN CALCULATION

in gmsin Newton

in Kmph

in m/s DESIGNER INPUTS

metres CALCULATED VALUE

K

kg/m3

N-s/m2

in N/m2

in Kg/m2 (FOR GLIDING W/S= 2.4 to 4.2 Kg/m2)

in m2

in metre 161.684909 in Cm

(FOR RECTANGULAR WING TAPPER RATIO =1)

in metre 10.10531 in Cm

in metre 10.10531 in Cm

in metre 10.1053068 in Cm

in metre 103.2036849

IL SIZING

in cm (AERODYNAMIC CENTRE LOCATES AT QUARTER CHORD POINT)

in cm

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in sq metre

(Aspect Ratio for horizontal tail" 6 to 10")

in Cm

in Cm

in sq metre

(Aspect Ratio for vertical tail" 1.5 to 2")

in Cm

in Cm

DESIGNKmph

in m/s

CL OF A/F 0.81

CL OF WING 0.7940063

in Newton L/D 17.40199563

in Watts

in HP

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Design & Developed By

(K.Selvaraju )AERONAUTICAL DEVELOPMENT AGENGY

(August 2011)

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Cd CL CD,0

0.061643166 -1 0.018420471

0.053430854 -0.9 0.018420471

0.046082996 -0.8 0.018420471

0.039599592 -0.7 0.018420471

0.033980641 -0.6 0.018420471

0.029226145 -0.5 0.018420471

0.025336102 -0.4 0.018420471

0.022310514 -0.3 0.018420471

0.020149379 -0.2 0.018420471

0.018852698 -0.1 0.018420471

0.018420471 -1.4E-16 0.018420471

0.018852698 0.1 0.018420471

0.020149379 0.2 0.018420471

0.022310514 0.3 0.018420471

0.025336102 0.4 0.018420471

0.029226145 0.5 0.018420471

0.033980641 0.6 0.018420471

0.039599592 0.7 0.018420471

0.046082996 0.8 0.018420471

0.053430854 0.9 0.018420471

0.061643166 1 0.0184204710.070719931 1.1 0.018420471

0.080661151 1.2 0.018420471

0.091466825 1.3 0.018420471

0.103136952 1.4 0.018420471

0.115671534 1.5 0.018420471

0.129070569 1.6 0.018420471

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0.143334058 1.7 0.018420471

0.158462001 1.8 0.018420471

0.174454398 1.9 0.018420471

0.191311249 2 0.018420471

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K

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.043222690.04322269

0.04322269

0.04322269

0.04322269

0.04322269

0.04322269

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0.04322269

0.04322269

0.04322269

0.04322269