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LoginThe zero-lift angle of attack for a thin, cambered airfoil increases in magnitude with the increasing camber of the airfoil.
(a) True
(b) False
The question was asked by my school principal while I was bunking the class.
This key question is from The Cambered Airfoil topic in division Incompressible Flow over Airfoils of Aerodynamics
Aerodynamics Incompressible Flow over Airfoils in Aerodynamics 3 years ago
The correct ANSWER is (a) True
To explain I would say: USING the formula for αL=0=\(\frac {-1}{\pi}\int_0^{\pi}\frac {dz}{dx} \)(cos∅-1)d∅, the DEPENDENCE of the zero-lift angle of ATTACK on camber can be seen. It is clear that for higher cambered AIRFOILS, αL=0 shifts to the negative side.
Posted on 02 Dec 2021, this text provides information on Aerodynamics related to Incompressible Flow over Airfoils in Aerodynamics. Please note that while accuracy is prioritized, the data presented might not be entirely correct or up-to-date. This information is offered for general knowledge and informational purposes only, and should not be considered as a substitute for professional advice.
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