Geometric and Performance Data of a Vigilante RA-C5 Aircraft

A three-view diagram of an RA-C5 Vigilante aircraft is shown in Figure 9.16. The following pertinent geometric and performance parameters are from [3]: two crew; engine: 2 x turbo-jet GE J-79-8(N), 75.6 kN; wingspan: 16.2 m; length: 22.3 m; height:

5.9 m; wing area: 65.0 m2; start mass: 27,300 kg; max speed: Mach 2+; ceiling: 18,300 m; range: 3,700 km; armament: nuclear bombs and missiles (only a clean configuration is evaluated).

Fuselage

• fuselage length = 73.25 ft

• average diameter at the maximum cross-section = 7.785 ft

• fuselage length/diameter = 9.66 (fineness ratio)

• fuselage upsweep angle = 0 deg

• fuselage closure angle « 0 deg

Wing

• planform reference area, SW = 65.03 m2 (700 ft2)

• span = 16.2 m (53.14 ft)

• aspect ratio = 3.73 deg

• t/c = 5%

Table 9.16. Bizjet total aircraft drag coefficient, CD

CL

0.2

0.3

0.4

0.5

0.6

0.7

CDpmin

ACDp (Table 9.6)

0.0003

0.00006

0

0.0205 (Table 9.5) 0.0006 0.0020

0.0040

Cmt (Table 9.7)

0.0017

0.00382

0.0068

0.0106

0.0153

0.0206

Total aircraft CD @ LRC

0.0225

0.02438

0.0273

0.0317

0.0378

0.0451

Wave drag, CDw (Figure 9.9)

0.0014

0.00170

0.0020

0.0025

0.0032

0.0045

Total aircraft CD @ HSC

0.0240

0.02618

0.0293

0.0342

0.0410

0.0496

Figure 9.14. Drag polar of Figure 9.1 plotted C2l versus CD

• taper ratio, X = 0.19

• camber = 0

• wing MAC = 4.63 m (15.19 ft)

• А/ = 37.5 deg

• Ale = 43 deg

• root chord at centerline = 6.1 m (20 ft)

• tip chord = 1.05 m (3.46 ft)

Empennage

• V-tail

• Sv = 4.4 m2 (47.34 ft2)

• span = 3.6 m (11.92 ft)

• MAC = (8.35 ft)

• t/c 4%

• H-tail

• Sh = 6.063 m2 (65.3 ft2)

• span = 9.85 m (32.3 ft)

• MAC = (9.73 ft)

• t/c = 4%

Nacelle/pylon (the engine is buried in the fuselage – no nacelle pylon)

• aircraft cruise performance, where the basic drag polar must be computed

• drag estimated at cruise altitude = 36,152 ft

• Mach number = 0.6 (has compressibility drag)

• ambient pressure = 391.68 lb/ft2

• Re/ft = 1.381 x 106

• design CL = 0.365

• design Mach number = 0.896 (Mcrit is at 0.9)

• maximum Mach number = 2.0

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