Effects of STOL Thrust Reversers and Powered Lift on Inlet Flow Quality 740457
An experimental test program was conducted to determine the engine environment which results from STOL operation with blown flaps and thrust reversers. Testing was conducted in a low speed wind tunnel with a 1/11 scale model of a STOL transport consisting of a fuselage and high-lift wing with triple-slotted externally blown flaps, leading edge slats, and powered model engines. Steady-state and dynamic total pressure distortion were moderate at takeoff and approach conditions with blown flaps. The cascade type STOL thrust reversers tested produced severe dynamic distortion due to unstable interactions of the reversed streams with the oncoming flow and vortex ingestion. Comments on methods to alleviate these problems are presented.
Citation: Sherman, D. and Usab, W., "Effects of STOL Thrust Reversers and Powered Lift on Inlet Flow Quality," SAE Technical Paper 740457, 1974, https://doi.org/10.4271/740457. Download Citation
Author(s):
Dale A. Sherman, William J. Usab
Affiliated:
Pratt & Whitney Aircraft Div., United Aircraft Corp.
Pages: 11
Event:
National Air Transportation Meeting
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
SAE 1974 Transactions-V83-A
Related Topics:
Thrust reversers
Scale models
Wind tunnel tests
Flaps
Fuselages
Wings
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