A practical procedure for the optimum design of transonic wings is demonstrated. The procedure uses an optimization program based on the method of feasible directions coupled with an aerodynamic analysis program which solves the three-dimensional potential equation for subsonic through transonic flow. Two new wings for the A-7 aircraft were designed by using the optimization procedure to achieve specified surface pressure distributions. The new wings, along with the existing A-7 wing, were tested in the Ames 11-foot transonic wind tunnel. The experimental data show that all of the performance goals were met.
Computational optimization and wind tunnel test of transonic wing designs
American Institute of Aeronautics and Astronautics, Aerospace Sciences Meeting ; 1979 ; New Orleans, LA
1979-01-01
Conference paper
No indication
English
Computational optimization and wind tunnel test of transonic wing designs
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