For an untwisted rectangular wing with an aspect ratio AR, the fundamental equation of Lifting Line...

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For an untwisted rectangular wing with an aspect ratio AR, the fundamental equation of Lifting Line Theory takes the form: 2b α(0₁) - α₁-0 (0o) = Σ( + c(0o)π sine) An sin neo. Here, the chord length c(00), the angle of attack a(00) and the angle of zero lift α=0(00) remain constant across the span. (a) When (00) - α=0(00) = 10 and AR-5, establish a system of linear equations to solve for the Fourier coefficients An. (b) Solve the linear systems using 00 = π 2π N'N, for N > 10 The spanwise distribution of circulation for the same wing be approximated as r = 4bv [0.02340 sin 0 + 0.00268 sin 30 +0.0072 sin 50 + 0.00010 sin 70], where b is the span and V is the free-stream speed. Calculate the lift and induced drag coefficient. can For an untwisted rectangular wing with an aspect ratio AR, the fundamental equation of Lifting Line Theory takes the form: 2b α(0₁) - α₁-0 (0o) = Σ( + c(0o)π sine) An sin neo. Here, the chord length c(00), the angle of attack a(00) and the angle of zero lift α=0(00) remain constant across the span. (a) When (00) - α=0(00) = 10 and AR-5, establish a system of linear equations to solve for the Fourier coefficients An. (b) Solve the linear systems using 00 = π 2π N'N, for N > 10 The spanwise distribution of circulation for the same wing be approximated as r = 4bv [0.02340 sin 0 + 0.00268 sin 30 +0.0072 sin 50 + 0.00010 sin 70], where b is the span and V is the free-stream speed. Calculate the lift and induced drag coefficient. can

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a Establishing the System of Linear Equations Substitute values AR 5 L0 10 Chord length c is constan... View the full answer