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Application of a one-strip integral method to the unsteady supersonic aerodynamics of an inclined flat surfaceThe method of integral relations is applied in a one-strip approximation to the perturbation equations governing small motions of an inclined, sharp-edged, flat surface about the mean supersonic steady flow. Algebraic expressions for low reduced-frequency aerodynamics are obtained and a set of ordinary differential equations are obtained for general oscillatory motion. Results are presented for low reduced-frequency aerodynamics and for the variation of the unsteady forces with frequency. The method gives accurate results for the aerodynamic forces at low reduced frequency which are in good agreement with available experimental data. However, for cases in which the aerodynamic forces vary rapidly with frequency, the results are qualitatively correct, but of limited accuracy. Calculations indicate that for a range of inclination angles near shock detachment such that the flow in the shock layer is low supersonic, the aerodynamic forces vary rapidly both with inclination angle and with reduced frequency.
Document ID
19720010339
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Technical Note (TN)
Authors
Bennett, R. M.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 2, 2013
Publication Date
March 1, 1972
Subject Category
Aerodynamics
Report/Patent Number
L-8047
NASA-TN-D-6644
Accession Number
72N17989
Funding Number(s)
PROJECT: RTOP 136-14-02-02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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