Master Of Science Aerospace Engineering

1Master Of Science Aerospace Engineering

Proyecto Final

“FRANKY”

2Master of Science in Aerospace engineering

PRIMER ESTIMADO DE PARAMETROS

FIRST ESTIMATE AR 5.333 ---e 0.89 ---k 0.067 ---

T 500 284.9 kP 500 95467.6 N/m2

Dens. 500 1.112 kg/m3weight (W0) 6.9 kgAltura (h) 500 mts.W fin 6.82 kg.R -gas 8314.32 J/K kmolm aire 28.96 kg/kmolR tierra 6356 km

g0 9.81 m/s2T0 288.15 KP0 101325 N/m2

Dens. 0 1.23 kg/m3W crew 0.46 kg.W Payload 2.07 kg.W Fuel 0.08 kg.Wempty 6.5 kg.

HorsePower 1.15 hpn fuel 0.065 ---E max 12.97 ---

Engine Power 825 lb*ft/segV max 37.27 ft/seg

V max 37.27 ft/seg

V max 11.43 m/seg.

Vel. Sonido (a) 336.43 J/kg

Mach Number (M) 0.05 m/s

K 1.07 ---

Re 1.50 ---

Log Re^2.58 0.01 ---

Cf .006 ---

A Superior 2.3 mts^2

A Lateral 1.8 mts^2

S wet 4.1 mts^2

a0 para 0' (Tabla 2.6) 0.11 grados

a0 radianes 6.0 Radianes

a (pendiente elev.) 1.2 por radian

a grados 0.1 Grados

Angulo ataque 4.0 Grados

CL 1.8 ---

C Di 0.028 ---

C D0 0.022 ---

CD 0.5 ---

D 21.3 ---

L 245.3 ---

E 11.5 ---


PRIMER ESTIMADO DE PARAMETROS

CARACTERISTICAS DEL ALA


CONFIGURACION DEL ALA


Aerospace Prototype Generation

PERFIL DEL ALAh

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PERFIL DEL ALA



ESTRUCTURA DEL ALA



ESTRUCTURA DEL ALA



ESTRUCTURA DEL ALA



ESTRUCTURA DEL ALA



ESTRUCTURA DEL ALA


PLANTILLAS DEL ALA



PLANTILLAS DEL ALA


CONFIGURACION DEL EMPENAJE

Empenaje Convencional

Tail Volume Ratios:

Horizontal Tail VHT= 0.7Vertical Tail: VvT = 0.04



CONFIGURACION DEL EMPENAGE

50.75 in

15.66 in

49.25 in

L HT


CONFIGURACION DEL EMPENAGE


Horizontal TailV HT 0.70 V VT 0.04 IHT 35.17 inIVT 30.59 in

c 11.25 inS HT 151.14 in^2SVT 63.0 in^2

AR for H TAIL 4.00

bt 24.59 inH Taper ratio

λ 0.50 crt 8.20 inctt 4.10 in

yHT 5.46 incHT 6.37 in


MODELADO DEL ALA HORIZONTAL



MODELADO DEL ALA HORIZONTAL



EMPENAJE



ESTRUCTURA




EMPENAJE



EMPENAJE



EMPENAJE



EMPENAJE



EMPENAJE


EMPENAJE


CALCULOS DE FUSELAJE


W data Weight UnitsW motor 1.22 lbsW Fuel 0.08 lbs

W S. Carburador 0.024 lbsW pila 0.05 lbs

W Tx. Y Servo ala 0.05 lbsW Baggage 2.07 lbs

Book-Dimentions ratio Nose/motor 2.0 in.Nose/Fuel 6.4 in.

Nose/S. Carburador 14.0 in.Nose/Pila 16.5 in.

Nose/Tx, S. ala 19 in.Nose/Baggage 24 in.

Effective c.g. of 3 weights without wing c.g. without wing Distance Units

x 15.66 in.Effective c.g. of 3 weights with wing

c.g. with wing Distance Unitsx 15.6 in.


Fuselage length

Wing Chord

c.g. w/o wing

c.g. with wingW

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W

En

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W

Bag

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EMPENAJE

15.66

50.75

11.25



Ratio UnitsNose-Ground 0.16 9.25 in

Nose-Wing inNose-a.c. inNose-c.g. 0.30 0.00 in

b 60 in cr 12.25 in *ct 12.25 in *y 15 c 12.25 in

Xn 16.81 in (Xac)wing 16.11 in

x 12.86 in Xc 18.98 in

Nosewheel 4.42 in



SG por requerimiento 60 mts

Vlo 37.988 ft/sSg= 22.557 /(t/w)R 257.793 ft

qob 8.75 gradosSa 39.214 ft

T/W 0.142 a 0.7 VloV 26.592 ft/s

Pr = T * V 45.249 ftlb/sP 60.332 ft lb/s

P min requerida 0.109694695 hp



UnitsVf 45.84 ft/sR 326.50 ft

sen 3' 0.05 ---cos 3' 0.999 ---tan 3' 0.05 ---

Obstacle 5 ftj 1.15 °µ 0.4 ---hf 0.457 ftSa 86.7 ftSf 17.1 ftSg 199.9 ft

Delta Cl max 0.5 Cl max 1.4765 CL max 1.32885

T/W 0.0864







Maximun Lift coefficient CL max = 1.8

Maximun Lift-to-Drag ratio (L/D) max = 12.97

Wing Loading W/S = 2.6 lb/ft²

Power Loading W/P = 31.1 lb/hp

Takeoff gross weight Wo = 12.0 lb

Fuel Weight Wf = 0.5 lb

Fuel tank Capacity 6.0 oz

Wing area S = 4.7 ft²

High-lift device

Zero-Lift drag coefficient CDO = 0.022

Arag due to lift coefficient K = 0.067

Aspect ratio AR = 5.333

Propeller efficiency ηpr = 0.75

Engine Power min P= 0.38 hp

Single-slotted trailing-edge flaps

CRITICAL PERFORMANCE PARAMETERS

PERFORMANCE PARAMETERS ESTIMATED

Documents

Master Of Science Aerospace Engineering