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Application of a full potential method for analysis of complex aircraft geometries

Author
Jones, Kenneth M.
Published
Dec 1, 1986.
Physical Description
1 electronic document
Additional Creators
Talcott, Noel A., Jr.
Online Version

Availability

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Restrictions on Access
Unclassified, Unlimited, Publicly available.
Free-to-read Unrestricted online access
Summary
A supersonic potential flow solver was developed to analyze the flow over complex realistic aircraft geometries. Enhancements to the method were made to accommodate regions of subsonic flow, the effect of trailing wakes on other aircraft components, and the modeling/gridding of complete configurations. Validation of the method was demonstrated by comparisons with experimental aerodynamic force and surface pressure measurements. The predicted results are in very good agreement with the experimental data. The bibliography contains additional information on the use of the potential flow code to predict the aerodynamics of high-speed wing/body configurations, waverider concepts, TAV, and the Space Shuttle orbiter package.
Other Subject(s)
Collection
NASA Technical Reports Server (NTRS) Collection.
Note
Document ID: 19880005548.
Accession ID: 88N14930.
Langley Symposium on Aerodynamics, Volume 1; p 73-87.
Terms of Use and Reproduction
No Copyright.
View MARC record | catkey: 15696202