The Fluidic Injection Nozzle Technology program is a national
cooperative effort to develop fluidic area control and thrust
vectoring concepts for advanced exhaust systems. Exhaust nozzles
with vector flow capability will increase the maneuverability
and survivability of future fighter aircraft. Currently used
mechanical vectoring and area-control systems add weight and
complexity to aircraft exhaust systems. With the use of fluidic
injection, area-control and vectoring can be achieved without
the added weight penalty. Under this program, the NASA Lewis Research
Center entered into a cooperative test program with Pratt &
Whitney to study the performance of the F119 nozzle with fluidic
injection. Our area of interest was to measure flow and thrust
coefficients, throat-area reduction, and vector angles.
This experimental program was successfully completed in January
1996 in Lewis' CE-22 facility. Various nozzle throat areas and
expansion ratios were tested over a wide range of nozzle pressure
ratios. Other model configurations included different injection
locations at different injection angles. Results confirmed that
fluidic injection is feasible in throat-area reduction and in
vectoring. The data obtained from this test program were added
to the current database, which can then be used to validate any
future performance prediction methodology and computational fluid
dynamics (CFD) analysis.
Previous articleLast updated April 29, 1997
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