Aerospace Engineering > GATE 2011 > Lifting Line Theory
Prandtl’s lifting line equation for a general wing is given by
where U∞ is the free-stream velocity, α is the angle of attack,
y0 is the spanwise location, αL=0(y0) gives the spanwise variation of zero-lift angle,
c is the chord, b is the span, and Γ(y0) gives the spanwise variation of circulation.
Given that
, the corresponding lift curve-slope is
∂CL/∂α is
where U∞ is the free-stream velocity, α is the angle of attack,
y0 is the spanwise location, αL=0(y0) gives the spanwise variation of zero-lift angle,
c is the chord, b is the span, and Γ(y0) gives the spanwise variation of circulation.Given that
, the corresponding lift curve-slope is∂CL/∂α is
Correct : a
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