Advanced Short Takeoff/Vertical Landing (STOVL) aircraft which can operate from remote locations, damaged runways, and small air capable ships are being pursued for deployment around the turn of the century. To achieve this goal, NASA Lewis Research Center, McDonnell Douglas Aircraft, and DARPA defined a cooperative program for testing in the NASA Lewis 9- by 15-foot low speed wind tunnel (LSWT) to establish a database for hot gas ingestion, one of the technologies critical to STOVL. Results are presented which show the engine inlet distortions (both temperature and pressure) in a 9.2 percent scale vectored thrust STOVL model in ground effects. Results are shown for the forward nozzle splay angles of 0 degrees, -6 degrees, and 18 degrees. The model support system had 4 degrees of freedom, heated high pressure air for nozzle flow, and a suction system exhaust for inlet flow. The headwind (freestream) velocity was varied from 8 to 23 knots.
Engine Inlet Distortion in a 9.2 Percent Scale Vectored Thrust STOVL Model in Ground Effect
1989
24 pages
Report
No indication
English
Aerodynamics , Aircraft , Fluid Mechanics , Jet & Gas Turbine Engines , Laboratory & Test Facility Design & Operation , Distortion , Engine inlets , Ground effect (Aerodynamics) , Nozzle flow , Scale models , Thrust , V/STOL aircraft , Data bases , Degrees of freedom , Free flow , High pressure , High temperature gases , Inlet flow , Low speed wind tunnels , Mcdonnell douglas aircraft , Position (Location) , Runways , Suction
The Synthesis of Ejector Lift/Vectored Thrust for STOVL
SAE Technical Papers | 1987
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