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An experimental investigation of nacelle-pylon installation on an unswept wing at subsonic and transonic speeds
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Compton II, W. B. Carlson, J. R. |
| Copyright Year | 1984 |
| Description | A wind tunnel investigation was conducted to determine the aerodynamic interference associated with the installation of a long duct, flow-through nacelle on a straight unswept untapered supercritical wing. Experimental data was obtained for the verification of computational prediction techniques. The model was tested in the 16-Foot Transonic Tunnel at Mach numbers from 0.20 to 0.875 and at angles of attack from about 0 deg to 5 deg. The results of the investigation show that strong viscous and compressibility effects are present at the transonic Mach numbers. Numerical comparisons show that linear theory is adequate for subsonic Mach number flow prediction, but is inadequate for prediction of the extreme flow conditions that exist at the transonic Mach numbers. |
| File Size | 19510511 |
| Page Count | 204 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19840010094 |
| Archival Resource Key | ark:/13960/t4fn61113 |
| Language | English |
| Publisher Date | 1984-02-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Unswept Wings Transonic Wind Tunnels Wind Tunnel Tests Aerodynamic Interference Supercritical Wings Transonic Speed Nacelles Angle of Attack Prediction Analysis Techniques Mach Number Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science |
| Content Type | Text |
| Resource Type | Technical Report |
