The internal performance of an axisymmetric convergent-divergent nozzle and a nonaxisymmetric convergent-divergent nozzle, both of which utilized a gimbal type mechanism for thrust vectoring was evaluated in the Static Test Facility of the Langley 16-Foot Transonic Tunnel. The nonaxisymmetric nozzle used the gimbal concept for yaw thrust vectoring only; pitch thrust vectoring was accomplished by simultaneous deflection of the upper and lower divergent flaps. The model geometric parameters investigated were pitch vector angle for the axisymmetric nozzle and pitch vector angle, yaw vector angle, nozzle throat aspect ratio, and nozzle expansion ratio for the nonaxisymmetric nozzle. All tests were conducted with no external flow, and nozzle pressure ratio was varied from 2.0 to approximately 12.0.
Internal Performance of Two Nozzles Utilizing Gimbal Concepts for Thrust Vectoring
1990
128 pages
Report
Keine Angabe
Englisch
Tilting rotorcraft utilizing ducted fan thrust vectoring nozzles
Europäisches Patentamt | 2023
|Aerodynamics Performance Prediction of Thrust-Vectoring Nozzles
Online Contents | 1998
|