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.
The rate of change of circulation with angle of attack Γα=∂Γ/∂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.The rate of change of circulation with angle of attack Γα=∂Γ/∂α is
Correct : b
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