Zero lift angle

The zero lift angle is the angle of attack of a wing profile against the flow , at which neither lift nor downforce occurs (hence the index ). The zero lift angle depends on the aerodynamically effective camber and always has a negative value; with non-arched ( symmetrical ) or certain S-lay profiles it is zero degrees: ${\displaystyle \alpha _{0}}$ ${\displaystyle _{0}}$

${\displaystyle \alpha _{0}\leq 0}$

The zero lift angle also strongly determines the maximum lift.

Since the increase in lift ΔCa / Δα is approximately the same for all profiles, the zero lift angle and zero angle lift are proportional : ${\displaystyle C_{\mathrm {a} 0}}$

minus 1 degree angle of attack corresponds to plus 0.11 . ${\displaystyle C_{\mathrm {a} 0}}$

swell

• Schmitz, FW; Aerodynamics of the flight model; Aero, 1983, ISBN 3-934596-08-8
• Abbott, I.; v. Doenhoff, AE: Theory of Wing Sections; New York, 1949; ISBN 0-486-60586-8
• Althaus, D., Wortmann, FX: Stuttgart profile catalog; Braunschweig, 1981; ISBN 3-528-08464-2