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Computational simulation of flows about hypersonic geometries with sharp leading edges

Authors :
Jones, Kevin D
Dougherty, F. Carroll
Publication Year :
1990
Publisher :
United States: NASA Center for Aerospace Information (CASI), 1990.

Abstract

Hypersonic waverider design has become an important concern in the aerospace industry. As one part of an inverse design effort for waveriders, work has been done to apply existing Euler and Navier-Stokies flow solvers to hypersonic geometries with sharp leading edges. Previously, calculations were done on bodies with rounded leading edges or with conical solutions for the nose initial conditions. In this paper, solutions are computed about waveriders and conical shapes with sharp leading edges without resorting to either shortrcut. All solutions show attached shocks with fully supersonic flows at the nose and along the leading edges. Flows about several waverider shapes are shown, as well as a preliminary cone with inlet calculation to study the shock/inlet interaction.

Subjects

Subjects :
Aerodynamics

Details

Language :
English
Database :
NASA Technical Reports
Notes :
NAG1-880
Publication Type :
Report
Accession number :
edsnas.19900058836
Document Type :
Report