An investigation was conducted in the Langley 16-Foot Transonic Tunnel to determine installation effects on single-engine convergent-divergent nozzles applicable to reduced-power supersonic cruise aircraft. Tests were conducted at Mach numbers from 0.50 to 1.20, at angles of attack from -3 degrees to 9 degrees, and at nozzle pressure ratios from 1.0 (jet off) to 8.0. The effects of empennage arrangement, nozzle length, a cusp fairing, and afterbody closure on total aft-end drag coefficient and component drag coefficients were investigated. Basic lift- and drag-coefficient data and external static-pressure distributions on the nozzle and afterbody are presented and discussed.
Investigation of installation effects of single-engine convergent-divergent nozzles
1982-11-01
Report
No indication
English
Aeroacoustic Resonance with Convergent-Divergent Nozzles
British Library Conference Proceedings | 1999
|Aeroacoustic resonance with convergent-divergent nozzles
AIAA | 1999
|