DEVELOPMENT OF A 3-DIMENSIONAL UPWIND PARABOLIZED NAVIER-STOKES CODE

The design of future hypersonic flight vehicles will depend heavily on computational fluid dynamics for the prediction of aerodynamic and thermodynamic loads as well as engine performance. One of the features that characterizes the hypersonic flow regime is the presence of strong shock waves generated by the vehicle and by protuberances from the main body such as wings, canopies, and engine inlets. Thus, a need exists for a robust computational tool that can efficiently and accurately resolve flowfields containing discontinuities. In the present work, an upwind algorithm designed for the integration of the parabolized Navier-Stokes (PNS) equations1 has been extended to three dimensions. Conventional PNS solvers are based on the central differencing of crossflow fluxes and, therefore, have difficulty capturing strong embedded shocks. The objective of this work is to mate the efficiency of the space-marching approach with the advantageous shockcapturing characteristics of upwind schemes. In addition to being upwind, the new algorithm is implicit (including boundary conditions) and is based on the use of finite volumes for accurate flux conservation. The new code is applied to laminar hypersonic flows past two simple body shapes: a circular cone of 10-deg half-angle and a generic all-body hypersonic vehicle. Cone flow solutions were computed at angles of attack of 12, 20, and 24 deg, and results are in good agreement with experimental data. Results also were obtained for the flow past the all-body vehicle at angles of incidence of 0 and 10 deg. © 1990 American Institute of Aeronautics and Astronautics, Inc., All rights reserved.