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Airfoils and Wings

1 tool in the Aerodynamics area.

Airfoil and Wing Lift

Section and wing lift from thin-airfoil theory and Prandtl's lifting line: the zero-lift angle, ideal angle, design lift coefficient and quarter-chord moment of a NACA four-digit camber line (or a flat plate, or an entered a0 and α_L0) from the thin-airfoil integrals in closed form; the planform as a straight taper or a typed chord and twist table; the monoplane equation solved at Multhopp stations as a linear system for the Fourier coefficients of the circulation, giving C_L, the induced drag C_Di, the induced-drag factor δ and span efficiency e, the lift-curve slope a with Glauert's τ, the wing zero-lift angle, the additional and basic (twist) distributions of c c_l and c_l along the span with the station where the section c_l,max is reached first, Schrenk's approximation beside the exact distribution, an optional wing-body factor, a planform figure and charts of the span loading and the lift curve. The default is a NACA 2412 wing of aspect ratio 8 and taper 0.5 with 3° of washout at 5° angle of attack: α_L0 −2.08°, C_L 0.501, C_Di 0.0103, e 0.972, a 4.97 per radian; the test reproduces Glauert's rectangular-aerofoil tables, NACA Report 572 and the mean-line data of NACA Report 824.

1 worked example reproduced, listed on the tool page.

Other Aerodynamics sections

Rotors and Propellers · Aircraft Performance · Stability and Control · Atmosphere and Flight Conditions · Propulsion