An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on convergent-divergent nozzles applicable to twin-engine reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, angles of attack from -5 deg to 9 deg, and at nozzle pressure ratios from jet off (1.0) to 8.0. The effects of empennage arrangement, nozzle length, and afterbody closure on total and component drag coefficients were investigated.
Investigation of Installation Effects on Twin-Engine Convergent-Divergent Nozzles
1983
191 pages
Report
No indication
English
Aeroacoustic Resonance with Convergent-Divergent Nozzles
British Library Conference Proceedings | 1999
|Aeroacoustic resonance with convergent-divergent nozzles
AIAA | 1999
|