Nomenclature b =wing semispan c = speed of sound M — Mach number Mc — Mach number of velocity component normal to ray from wing apex Ms = Mach number of velocity component normal to upstream side of shock p = pressure S5 = (shock spanwise location)/Z? s = entropy, in (p/p^) ~ 7&i(p/P« a = angle of attack A = wing sweep angle measured from normal to wing centerline p = density EI\ = (z component of total crossflow plane circulation)/^^ >)