Flight tests recently completed at the NASA Dryden Flight Research Center evaluated performance of a hydromechanically vectored axisymmetric nozzle onboard the F-15 ACTIVE. A flight-test technique whereby strain gages installed onto engine mounts provided for the direct measurement of thrust and vector forces has proven to be extremely valuable. Flow turning and thrust efficiency, as well as nozzle static pressure distributions were measured and analyzed. This report presents results from testing at an altitude of 30,000 ft and a speed of Mach 0.9. Flow turning and thrust efficiency were found to be significantly different than predicted, and moreover, varied substantially with power setting and pitch vector angle. Results of an in-flight comparison of the direct thrust measurement technique and an engine simulation fell within the expected uncertainty bands. Overall nozzle performance at this flight condition demonstrated the F100-PW-229 thrust-vectoring nozzles to be highly capable and efficient.
Selected Performance Measurements of the F-15 ACTIVE Axisymmetric Thrust-Vectoring Nozzle
1999
12 pages
Report
Keine Angabe
Englisch
Aircraft , F-15 aircraft , Thrust vector control , Flight tests , Thrust measurement , Nozzle geometry , Subsonic speed , Nozzle flow , Performance tests , Pressure distribution , Flight conditions , Strain gages , Nozzle efficiency , Nozzle thrust coefficients , Static pressure , Aerodynamic loads , Flow distribution
Selected Performance Measurements of the F-15 ACTIVE Axisymmetric Thrust-Vectoring Nozzle
British Library Conference Proceedings | 1999
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