论文信息 - Influence of Shape Parameterization on Aerodynamic Shape Optimization

Influence of Shape Parameterization on Aerodynamic Shape Optimization

Sref b Wing Span B Shape Function Basis CFD Computational Fluid Dynamics CD Drag Coefficient = Drag q∞Sref CL Lift Coefficient = Lift q∞Sref CM Pitching-Moment Coefficient = Moment q∞Sref Cref Cmax Maximum Camber of an Airfoil Cref Wing Reference Chord count Drag Coefficient Unit = 0.0001 DTE Divergent Trailing Edge FRP Fuselage Reference Plane I Objective or Cost Function K Order of Bezier or B-Spline Curve LE Leading-Edge Point per MLL MAC Mean Aerodynamic Chord MLL Maximum Length Line = Chordline N, NDV Number of Design Variables RANS Reynolds-Averaged Navier-Stokes Re Wing Reynolds number based on Cref Sref Wing Reference Area TE Trailing-Edge Point = 1 2 (TEu + TEl) TEBase Trailing-Edge Base Height = yteu − ytel Tmax Maximum Thickness of an Airfoil WRP Wing Reference Plane x, y, z Spatial Coordinates xcpt, ycpt X-Y Coordinates of a Control Point q Dynamic Pressure = 1 2 ρV 2 λ Wing Taper Ratio = Ctip Croot Λc/4 Wing Quarter-Chord Sweep π 3.141592654... ∞ Infinity O(∗) Order of

John C. Vassberg | Antony Jameson

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