Conceptual Aircraft Design

Appendix DSome Case Studies – Aircraft Data

D.1. Airbus320 Class Aircraft

All computations carried out here follow the book's instructions. The results are not from Airbus Industry and they are not responsible for the figures given here. This is used only to substantiate the book methodology with the industry values to gain some confidence. Industry drag data is not available but, at the end, whether payload‐range matches with the published data should be checked.

Given:

Long range cruise (LRC) speed and Altitude: Mach 0.75 at 36 089 ft.

Figure D.1 shows a three‐view diagram of an Airbus320.

Figure D.1 Airbus 320 three‐view with major dimensions (courtesy of Airbus). Reproduced permission of John Wiley and CUP.

D.1.1 Dimensions (to Scale the Drawing for Detailed Dimensions)

Fuselage: Length = 123.16 ft (scaled measurement differed slightly from the drawings).

Fuselage width = 13.1 ft, Fuselage depth = 13 ft.

Wing reference area (trapezoidal part only) = 1202.5 ft², Add the yehudi area = 118.8 ft².

Span = 11.85 ft, MAC_wing = 11.64 ft, AR = 9.37, Λ_¼ = 25°, C_R = 16.5 ft, λ = 0.3, t/c_ave = 0.12.

H‐tail reference area = 330.5 ft², MAC_H‐tail = 8.63 ft.

V‐tail reference area = 235.6 ft², MAC_V‐tail = 13.02 ft.

Nacelle length = 17.28 ft, Maximum diameter = 6.95 ft.

Pylon = to measure from the drawing.

Reynolds number per foot is given by, Re_{per foot} = (Vρ)/μ = (aMρ)/μ.

=[(0.75 × 968.08)(0.000 71)]/(0.795 0 × 373.718 × 10 ...