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Interactive boundary-layer calculations of a transonic wing flowResults obtained from iterative solutions of inviscid and boundary-layer equations are presented and compared with experimental values. The calculated results were obtained with an Euler code and a transonic potential code in order to furnish solutions for the inviscid flow; they were interacted with solutions of two-dimensional boundary-layer equations having a strip-theory approximation. Euler code results are found to be in better agreement with the experimental data than with the full potential code, especially in the presence of shock waves, (with the sole exception of the near-tip region).
Document ID
19890044496
Document Type
Reprint (Version printed in journal)
Authors
Kaups, Kalle (Douglas Aircraft Co., Inc. Long Beach, CA, United States)
Cebeci, Tuncer (Douglas Aircraft Co. Long Beach, CA, United States)
Mehta, Unmeel (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 14, 2013
Publication Date
April 1, 1989
Publication Information
Publication: Journal of Aircraft
Volume: 26
ISSN: 0021-8669
Subject Category
AERODYNAMICS
Distribution Limits
Public
Copyright
Other