The design of the propulsion system installation affects strongly the total drag and overall performance of an aircraft, and the concept, placement, and integration details of the exhaust nozzle are major considerations in the configuration definition. As part of the NASA Supersonic Cruise Research (SCR) program, a wind tunnel test program has been conducted to investigate exhaust nozzle-airframe interactions at transonic speeds. First phase testing is to establish guidelines for follow-on testing. A summary is provided of the results of first phase testing, taking into account the test approach, the effect of nozzle closure on aircraft aerodynamic characteristics, nozzle installation effects and nacelle interference drag, and an analytical study of the effects of nozzle closure on the aircraft.
Transonic wind tunnel test of a supersonic nozzle installation
Joint Propulsion Conference ; 1982 ; Cleveland, OH
1982-06-01
Conference paper
No indication
English
NACA transonic wind tunnel test sections
SLUB | 1956
|NACA transonic wind-tunnel test sections
Engineering Index Backfile | 1955
|NACA transonic wind-tunnel test sections
TIBKAT | 1955
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