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Investigation of a supersonic cruise fighter model flow field
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Reubush, D. E. Bare, E. A. |
| Copyright Year | 1985 |
| Description | An investigation was conducted in the Langley 16-Foot Transonic Tunnel to survey the flow field around a model of a supersonic cruise fighter configuration. Local values of angle of attack, side flow, Mach number, and total pressure ratio were measured with a single multi-holed probe in three survey areas on a model previously used for nacelle/nozzle integration investigations. The investigation was conducted at Mach numbers of 0.6, 0.9, and 1.2, and at angles of attack from 0 deg to 10 deg. The purpose of the investigation was to provide a base of experimental data with which theoretically determined data can be compared. To that end the data are presented in tables as well as graphically, and a complete description of the model geometry is included as fuselage cross sections and wing span stations. Measured local angles of attack were generally greater than free stream angle of attack above the wing and generally smaller below. There were large spanwise local angle-of-attack and side flow gradients above the wing at the higher free stream angles of attack. |
| File Size | 7278970 |
| Page Count | 156 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19860005778 |
| Archival Resource Key | ark:/13960/t0xq1w65n |
| Language | English |
| Publisher Date | 1985-11-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Aircraft Models Tables Data Transonic Flow Supersonic Aircraft Aerodynamic Configurations Flow Distribution Wind Tunnel Tests Nacelles Angle of Attack Fighter Aircraft Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
