1. The numerical method used forsolvingthe 2-0VSL equationsisthe same asthat employed foraxisymmetric b d i e s . However,the shock standoffdlstancensh ataspecifiedbody station. m. isobtained from the integration ofEq. (1) where
2. The Vigneron condition 3 isirsed for the pressure gradient in the streamwise momenttoil equation in the subsonic nose region. Theglolxil iteratlons areemployed In this region to upd;iit. the pressure (andshockshape). In the supersixik flowregion, the pressure gradlent term is approximated with a two-point backward differenceand apredlctoi-correctorapproacli:',iii used for the shockshape tomarch the solutio,^ downstream. It should be mentioned here th:tl unlike the axisymmetric calculations 3-6 convergedresults cannot be obtained for the :i 11 shape without the use ofvigneron condition.