An aerodynamic analysis of the generic hypersonic vehicle

The idealized generic hypersonic vehicle (GHV) configuration is modeled as an elementary aircraft with a fully integrated scramjet. In this analysis, its aerothermodynamic performance is numerically evaluated. The objectives of this effort are to conduct detailed fluid dynamic simulations of the hypersonic flow fields within and around the GHV. In addition, the GHV on- and off-design performance analyses, relative to freestream Mach Numbers and angles of attack, were conducted. The baseline computational simulations of the GHV configuration were conducted at a Mach number of 6, and at a dynamic pressure of 1500 psf along the hypersonic flight path. These objectives were accomplished through the use of two independent computational fluid dynamic studies. In the case of the first study; simulating the coupled internal and external GHV flow, grid generation efforts were accomplished by using the NUMECA™ hexpress hybrid software. In the second study, two sets of CFD analyses were conducted in simulating the GHV internal flow. The GHV scramjet was first modeled with a cylindrical combustor and its internal ‘clean flow path’ analyzed. This was followed by the CFD analysis of the GHV scramjet with a ‘realistically modified’ combustor. During the internal flow path studies, the grid generation efforts were conducted using Gridgen™. In both sets of analyses, the fluid dynamic simulations were conducted using the AVUS Navier-Stokes solver. The CFD studies included simulations under inviscid, laminar and turbulent flow field conditions.