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Delta wings with shock-free cross flowIn order to have a high level of maneuverability, supersonic delta wings should have a cross flow that is free of embedded shock waves. The conical cross flow sonic surface differs from that of plane transonic flow in many aspects. Well-known properties such as the monotone law are not true for conical cross flow sonic surfaces. By using a local analysis of the cross flow sonic line, relevant conditions for smooth cross flow are obtained. A technique to artificially construct a smooth sonic surface and an efficient numerical method to calculate the flow field are used to obtain cones with smooth cross flow.
Document ID
19840011214
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Sritharan, S. S. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
February 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-172297
REPT-84-6
NAS 1.26:172297
Accession Number
84N19282
Funding Number(s)
CONTRACT_GRANT: NAS1-17070
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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