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Computational simulation of flows about hypersonic geometries with sharp leading edgesHypersonic 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.
Document ID
19900058836
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Jones, Kevin D.
(Colorado Univ. Boulder, CO, United States)
Dougherty, F. Carroll
(Colorado, University Boulder, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1990
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 90-3065
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Portland, OR
Country: United States
Start Date: August 20, 1990
End Date: August 22, 1990
Accession Number
90A45891
Funding Number(s)
CONTRACT_GRANT: NAG1-880
Distribution Limits
Public
Copyright
Other

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