ENHANCEMENTS TO VISCOUS-SHOCK-LAYER TECHNIQUE

A solution procedure is presented that considerably improves the compu tational efficiency of the viscous-shock-layer technique, especially f or long slender bodies. The ''predictor-corrector'' procedure suggeste d for obtaining the shock shape beyond the nose region requires only a single global pass. The accuracy of the present method is demonstrate d by comparison with globally iterated results over the entire body an d with ground- and flight-test data. The new procedure results in comp uter run times one-third to one-half of the times required for the ful l-body global iteration procedure. Furthermore, the algebraic expressi ons used to specify the initial shock shape eliminate the need for a s hock shape generated by external means and permit immediate introducti on of the full viscous-shock-layer equations.