Numerical investigation of supersonic vortical flow about a missile body

Three-dimensional supersonic viscous flow computations including crossflow separation are presented for an ogive-cylinder at an angle of attack varying from 0 to 20 deg. Solutions are obtained for the parabolized Navier-Stokes equations from an algorithm that incorporates a fully upwind implicit approach. Results are presented for laminar flow assumption and include side-by-side comparison with wind-tunnel data. Excellent agreement is obtained between computations and wind-tunnel measurements at a freestream Mach number of 2 in terms of surface pressure distribution, body streamline pattern, and stagnation pressure contours in crossflow planes. (Author)