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Interactive design of hypersonic waverider geometriesThe paper deals with an inverse design code utilizing the method of oscillating cones; the code integrated into an interactive graphics software package allows manipulation of both the exit-plane shock profile and leading edge of the vehicle. Another interactive feature of the system is the ability to vary freestream conditions and reevaluate the governing conditions. The development of the oscillating cones is shown on five classes each of which is chosen to demonstrate an aspect of improved design flexibility over previous studies. Results are evaluated using a robust flow solver, insuring that the shock shapes specified in the design process are recovered. It is pointed out that the expanded range of waverider geometries that may be generated using the oscillating cones technique may provide insight into visually oriented optimization parameters such as volumetric efficiency and practical planform.
Document ID
19910058974
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Center, K. B.
(Colorado Univ. Boulder, CO, United States)
Sobieczky, H.
(Colorado Univ. Boulder, CO, United States)
Dougherty, F. C.
(Colorado, University Boulder, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1991
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA PAPER 91-1697
Accession Number
91A43597
Funding Number(s)
CONTRACT_GRANT: NAG1-880
Distribution Limits
Public
Copyright
Other

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