Zero angle lift

The zero-angle lift is the key figure of the dynamic lift of a wing profile at a flow angle of zero degrees to the chord . It depends on the aerodynamically effective curvature . Non-arched (symmetrical) or certain S-flapping profiles have no zero-angle lift. Profiles with a high maximum lift usually also have a large zero-angle lift. ${\displaystyle \!\,C_{\mathrm {a} 0}}$

Since the increase in lift is roughly the same for all profiles, the zero-angle lift and the zero-lift angle are proportional. An angle of attack of = −1 ° corresponds to a zero angle lift of . ${\displaystyle \Delta C_{\mathrm {a} }/\Delta \alpha }$ ${\displaystyle \alpha _{0}}$ ${\displaystyle \alpha }$ ${\displaystyle C_{\mathrm {a} 0}=0{,}11}$

swell

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