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Minimum Induced Drag For Tapered Wings Including Structural Constraints, Jeffrey D. Taylor, Douglas F. Hunsaker
Minimum Induced Drag For Tapered Wings Including Structural Constraints, Jeffrey D. Taylor, Douglas F. Hunsaker
Mechanical and Aerospace Engineering Student Publications and Presentations
LIFTING-LINE theory [1,2] is the foundation for much of our understanding of finite-wing aerodynamics. Solutions based on lifting-line theory are widely accepted and have been shown to be in good agreement with CFD [3-10]. From Prandtl’s analytic solution to the classical lifting-line equation [1,2], the wing section-lift distribution can be expressed as a Fourier series of the form [11]
bL~ (θ)/L = (4/π)[sin(θ) + Σ∞n-2 Bnsin(nθ)]; θ = cos-1(-2z/b) (1)
where b is the wingspan, L~ is the local wing section lift, L is the total wing lift, z is the spanwise …