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A comparison of theoretical and experimental pressure distributions for two advanced fighter wings
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Hicks, R. M. Haney, H. P. |
| Copyright Year | 1981 |
| Description | A comparison was made between experimental pressure distributions measured during testing of the Vought A-7 fighter and the theoretical predictions of four transonic potential flow codes. Isolated wind and three wing-body codes were used for comparison. All comparisons are for transonic Mach numbers and include both attached and separate flows. In general, the wing-body codes gave better agreement with the experiment than did the isolated wing code but, because of the greater complexity of the geometry, were found to be considerably more expensive and less reliable. |
| File Size | 2450272 |
| Page Count | 87 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19820003181 |
| Archival Resource Key | ark:/13960/t7pp3x962 |
| Language | English |
| Publisher Date | 1981-10-01 |
| Access Restriction | Open |
| Subject Keyword | Aircraft Design, Testing And Performance Transonic Flow Supersonic Aircraft Body-wing Configurations Finite Difference Theory Flow Distribution Pressure Distribution Supercritical Wings Separated Flow Computer Aided Design Optimization Computer Programs A-7 Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
