Computational fluid dynamics application to hypersonic flow over a Martian entry vehicle (MEV) - A correlation with experimentA class of vehicles for a mission to Mars are analyzed for aerodynamic characteristics using advanced Computational Fluid Dynamics (CFD). The general configuration is a modified cone-conical-frustum geometry where the nose radius has a large influence on the flowfield. Inviscid-compressible flow using the Euler equations and viscous-compressible flow using the thin-layer Navier-Stokes equations is applied to the configuration. The surface modeling, grid generation and application of state-of-the-art CFD software are described. The effects of nose radius, angle of attack, and hypersonic velocity on the flight characteristics of the vehicle are discussed. The numerical simulations demonstrate the merits of the inviscid and viscous software. Results are compared with wind tunnel experiments.
Document ID
19920046978
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Stewart, John E. (Computer Sciences Corp. Hampton, VA, United States)
Smith, Robert E. (NASA Langley Research Center Hampton, VA, United States)
Ashby, George C., Jr. (NASA Langley Research Center Hampton, VA, United States)