Predictions require less computation than Navier-Stokes solutions. RAXJET computer program predicts transonic, axisymmetric flow over nozzle afterbodies with supersonic jet exhausts and includes effects of boundarylayer displacement, separation, jet entrainment, and inviscid jet plume blockage. RAXJET written in FORTRAN IV.
Transonic, Axisymmetric Flow Over Nozzle Afterbodies With Supersonic Jet Exhausts
NASA Tech Briefs ; 7 , 4
01.10.1983
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Englisch