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EXHAUST-NOZZLE CHARACTERISTICS FOR A TWIN-JET VARIABLE-WING-SWEEP FIGHTER AIRPLANE MODEL AT MACH NUMBERS TO 2.2

机译：机编号为2.2的双喷射变速涡流飞机模型的排气喷嘴特性

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A wind-tunnel investigation has been conducted to determine the exhaust-nozzle aerody¬namic and propulsive characteristics for a twin-jet variable-wing-sweep fighter airplane model. The powered model was tested in the Langley 16-foot transonic tunnel and in the Langley 4-foot supersonic pressure tunnel at Mach numbers to 2.2 and at angles of attack from about -2° to 6°. Compressed air was used to simulate the nozzle exhaust flow at values of jet total-pressure ratio from approximately 1 (jet off) to about 21. Effects of configuration variables such as speed-brake deflection, store installation, and boundary-layer thickness on the nozzle characteristics were also investigated.

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作者
David E. Reubush; Charles E. Mercer;
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年度 1974
页码 1-138
总页数 138
原文格式 PDF
正文语种 eng
中图分类工业技术;
关键词
Jet engine exhaust nozzles - Jet effects - Airplane aerodynamics - Boattail drag;

机译：喷气发动机排气喷嘴 - 喷射效果 - 飞机空气动力学 - 船尾拖动;

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EXHAUST-NOZZLE CHARACTERISTICS FOR A TWIN-JET VARIABLE-WING-SWEEP FIGHTER AIRPLANE MODEL AT MACH NUMBERS TO 2.2

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