An experimental investigation of multiaxis thrust vectoring nozzles with spherical convergent flaps (SCF) and a convertible (in-flight deployable) centerline plug were tested in the NASA-Langley 16-Foot Transonic Tunnel Static Test Facility. Parameters tested during the static test included plug length, external shroud length, shroud internal angle, and yaw vector angle. Results indicated that the SCF convertible-plug nozzle flow is highly three dimensional and characterized by internal flow separation and shock effects. The resultant thrust and discharge coefficient levels were lower than previous wedge nozzle results. In addition, increasing shroud internal angle increased resultant thrust ratio but decreased discharge coefficient. Increasing shroud length increased resultant thrust ratio performance for NPR's greater than 6.0 but for NPR's less than 6.0, resultant thrust ratio decreased as shroud length increased. Increasing plug length caused an increase in resultant thrust ratio and an increase in discharge coefficient. Increasing geometric yaw vector angle had no effect on resultant thrust ratio and little effect on discharge coefficient.
Experimental investigation of spherical-convergent-flap thrust-vectoring two-dimensional plug nozzles
AIAA, SAE, ASME, and ASEE, Joint Propulsion Conference and Exhibit ; 1993 ; Monterey, CA, United States
01.06.1993
Aufsatz (Konferenz)
Keine Angabe
Englisch
Thrust Vectoring Control from Convergent Nozzles with Translating Side Wall
Online Contents | 1995
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