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An experimental investigation of propfan installations on an upswept supercritical wing at transonic mach numbers
| Content Provider | NASA Technical Reports Server (NTRS) |
|---|---|
| Author | Bartlett, G. R. |
| Copyright Year | 1985 |
| Description | An investigation has been conducted in the Langley 16 Foot Transonic Tunnel to determine propfan installation and slipstream interference effects on an unswept supercritical wing. This data can be used for verification of existing and developing theoretical codes as well as giving an understanding of the flow interactions associated with propeller/nacelle/wing integration. The investigation was conducted over a Mach number range of 0.5 to 0.8 and at angles of attack from 0 deg to 3 deg. The propeller was powered by an air turbine simulator and the exhaust from the air turbine was used to simulate the exhaust from the propfan nacelle. Reynolds number based on wing chord varied from 3 to 4 million. Results indicate that the propfan causes an increase in the wing lift coefficient. It was found that most of the propeller induced swirl is recovered by the wing. The propeller slipstream also causes a large favorable leading edge suction peak on the upwash side and a smaller unfavorable decrease on the downwash side. |
| File Size | 14922709 |
| Page Count | 208 |
| File Format | |
| Alternate Webpage(s) | http://archive.org/details/NASA_NTRS_Archive_19850022700 |
| Archival Resource Key | ark:/13960/t2b904t3d |
| Language | English |
| Publisher Date | 1985-05-01 |
| Access Restriction | Open |
| Subject Keyword | Aerodynamics Tables Data Propellers Wind Tunnel Tests Slipstreams Pressure Distribution Supercritical Wings Transonic Speed Nacelles Turbines 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 |
