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 su personic linearized theory modified to include corrections for attaina ble leading-edge thrust and vortex forces. A semiempirical design and estimation method has been developed to account for the deficiencies o f the linearized theory which tends to overestimate the required amoun t of twist and camber and predicts an unattainable level of performanc e. Comparisons of theoretical and experimental results showed that the semiempirical method provides for the selection of the amount of twis t and camber required for maximum performance at cruise and gives a go od estimate of the level of performance.