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The transonic aerofoil problem with embedded shocks.The integral equation approach to the mixed flow problem of infinite wings at high subsonic speeds is adopted for non-circulatory and circulatory (lifting) flows. The solutions are determined from a system of non-linear algebraic equations and, to ensure always unique solutions, the method of differentiation with respect to a parameter has been applied. The resulting Cauchy problem is then solved with the linearised flow solution as the initial value vector. For the case of embedded shocks in the flow field, the method of steepest descent has been added to the calculation scheme. Results for subcritical and supercritical flows past aerofoils are given and compared with solutions obtained by finite-difference techniques.
Document ID
19730046320
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Norstrud, H.
(Lockheed-Georgia Co. Marietta, Ga., United States)
Date Acquired
August 7, 2013
Publication Date
May 1, 1973
Publication Information
Publication: Aeronautical Quarterly
Volume: 24
Subject Category
Aerodynamics
Accession Number
73A31122
Funding Number(s)
CONTRACT_GRANT: NAS1-10665
Distribution Limits
Public
Copyright
Other

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