NASA NTRS · 19790055007
Static test of a large scale swivel nozzle thrust deflector
Abstract
Experimental results from a swivel nozzle thrust deflector test program are presented. The deflector was installed behind a 36-inch fan with a tip turbine hot gas drive. The maximum nozzle pressure ratio was 1.2. Nozzle thrust and flow coefficients are presented for a range of vectoring angles. The results are also compared to small scale cold flow test results. The comparison suggests a need for accurate simulation of nozzle entry pressure and temperature profiles on model tests.
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Federspiel, J. F.. 1979-06-01. Static test of a large scale swivel nozzle thrust deflector. https://ntrs.nasa.gov/citations/19790055007
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