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An initial investigation into methods of computing transonic aerodynamic sensitivity coefficientsContinuing studies associated with the development of the quasi-analytical (QA) sensitivity method for three dimensional transonic flow about wings are presented. Furthermore, initial results using the quasi-analytical approach were obtained and compared to those computed using the finite difference (FD) approach. The basic goals achieved were: (1) carrying out various debugging operations pertaining to the quasi-analytical method; (2) addition of section design variables to the sensitivity equation in the form of multiple right hand sides; (3) reconfiguring the analysis/sensitivity package in order to facilitate the execution of analysis/FD/QA test cases; and (4) enhancing the display of output data to allow careful examination of the results and to permit various comparisons of sensitivity derivatives obtained using the FC/QA methods to be conducted easily and quickly. In addition to discussing the above goals, the results of executing subcritical and supercritical test cases are presented.
Document ID
19910017816
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Carlson, Leland A. (Texas A&M Univ. College Station, TX, United States)
Date Acquired
September 6, 2013
Publication Date
July 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-188644
TAMRF-5802-91-02
NAS 1.26:188644
Accession Number
91N27130
Funding Number(s)
CONTRACT_GRANT: NAG1-793
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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