Airfoil design by numerical optimization using a minicomputer
Raymond Morton Hicks, C. A. Szelazek, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Ames Research Center, Computer Information Systems (Firm)
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978 - Computers - 24 pages
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aerodynamic analysis coupled aerodynamic changes due aerodynamic coefficients airfoil contours airfoil design code airfoil design program airfoil thickness Ames Research Center automated design auxiliary circle baseline airfoil class of airfoil COMPUTE Cg Computer Information Systems conjugate gradient Cupertino decrease the nose-down derivative of pitching DESIGN BY NUMERICAL desired pressure distribution developed figure 12 figure 9 figures 3—8 final design problem final profile finite difference Hicks Ames Research HP 9830 minicomputer initial airfoil initial profile inviscid ITERATION NUMBER Joukowski method lift coefficient constraint low speed low-speed airfoil sections minicomputer of low minimization with constraint Moffett Field NASA nose-down pitching numerical optimization algorithm objective function optimization process origin to center parabolas partial derivative penalty function Performing Organization perturbation pitching moment minimization pitching-moment minimization problem pressure coefficient Profile and aerodynamic Raymond reduction in nose-down shown in figure six design variables six parameters technique unconstrained pitching-moment minimization weighting factor weighting parameter