Three-dimensional Navier-Stokes simulations are made for the external flow, the jet-exhaust plume, and the internal nozzle flow of a nonaxisymmetric nozzle typical of those advocated for advanced fighter airplanes. Solutions are presented for free-stream Mach numbers of 0.80, 0.94, and 1.20 at an angle of attack of 0 deg and a Reynolds number of 20 x 10 to the 6th. Jet-total-pressure ratios ranging from 1.5 to 9.8, i.e., from below to above the design pressure ratio of 4.25, are investigated. The results are compared to wind-tunnel data. The calculations successfully predict many trends and features of the external and internal flow.
Navier-Stokes simulation of nozzle-afterbody flows with jets at off-design conditions
AIAA Applied Aerodynamics Conference
1991-01-01
Conference paper
No indication
English
NAVIER-STOKES COMPUTATIONS ON NOZZLE-AFTERBODY CONFIGURATIONS
British Library Conference Proceedings | 2003
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