 studi inviscid flow air foil high superson speed studi inviscid flow air foil high superson speed steadi flow curv airfoil high superson speed investig analytici assumpt air behav diatom ga shock-expans method predict flow curv airfoil extrem high mach number provid flow deflect angl close correspond shock detach result appli determin surfac pressur distribut determin flow field airfoil verif observ aid method characterist extens calcul pressur gradient shock-wave curvatur lead edg calcul pressur distribut 10-percent-thick biconvex airfoil 0 angl attack approxim shock-expans method thin airfoil high mach number investig yield pressur error 10 percent mach number three flow deflect angl 25 slender-airfoil method simpl form prove engin purpos effect calor imperfect air manifest disturb flow field high mach number investig attent reduct ratio specif heat long ratio decreas appreci includ effect imperfect accur ideal-ga flow observ verfi aid gener shock-expans method gener method characterist emploi form applic local air temperatur 5000 rankin slender-airfoil method modifi emploi averag ratio specif heat flow field simplifi method essenti accuraci imperfect-ga flow counterpart ideal-ga flow approxim flow analysi extrem high mach number indic ratio specif heat approach close 1 case shock-expans method consider error busemann method limit infinit free-stream mach number specif-heat ratio 1 appear appli reason accuraci 