AERODYNAMIC DESIGN OF SUPERSONIC CRUISE WINGS WITH A CALIBRATED LINEARIZED THEORY

The design of supersonic cruise wings for minimum drag due to lift is examined in this study. The aerodgnamic design method is based on a supersonic linearized theory modified to include corrections for attainable leading-edge thrust and vortex forces. A semiempirical design and estimation method has been developed to account for the deficiencies of the linearized theory which tends to overestimate the required amount of twist and camber and predicts an unattainable level of performance. Comparisons of theoretical and experimental results showed that the semiempirical method provides for the selection of the amount of twist and camber required for maximum performance at cruise and gives a good estimate of the level of performance.