Quarterly of Applied Mathematics

Quarterly of Applied Mathematics

Online ISSN 1552-4485; Print ISSN 0033-569X



Delta wings with shock-free cross flow

Author: S. S. Sritharan
Journal: Quart. Appl. Math. 43 (1985), 275-286
MSC: Primary 76H05; Secondary 76J99
DOI: https://doi.org/10.1090/qam/814226
MathSciNet review: 814226
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Abstract: It has been realized recently that in 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. Using a local analysis of the cross flow sonic line, relevant conditions for smooth cross flow are obtained. Using a technique to construct artificially a smooth sonic surface and an efficient numerical method to calculate the flow field, one obtains cones with smooth cross flow.

References [Enhancements On Off] (What's this?)

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DOI: https://doi.org/10.1090/qam/814226
Article copyright: © Copyright 1985 American Mathematical Society

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