Experimental and analytical investigation of axisymmetric supersonic cruise nozzle geometry at Mach numbers form 0.60 to 1.30
George T. Carson, Edwin E. Lee, Langley Research Center, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1981 - Medical - 86 pages
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16-Foot Transonic Tunnel afterburning analytically determined external axial boattail drag boattail pressure boattail pressure-drag coefficient Comparison of experimentally convergent-divergent nozzles design nozzle pressure design value determined external pressure discharge coefficients distributions for nozzle divergence angle divergent section drag coefficients equation exit area expansion ratios experimental data experimentally and analytically External and internal external pressure distribution free-stream Mach number gross thrust increasing internal performance internal surface-pressure distributions inviscid jet effects jet-exhaust Langley 16-Foot Transonic Langley Research Center maximum measured Method of Characteristics metric afterbody NASA nozzle configuration Nozzle cross-sectional contour nozzle exit nozzle geometry Nozzle internal pressure nozzle pressure ratio Nozzle throat numbers from 0.60 optimum expansion orifices overall force ratio overall performance schedule separated region shock wave shown in figure skin-friction drag static pressure static thrust coefficient subsonic speeds supersonic cruise aircraft Supersonic Cruise Research supersonic speeds tare throat area turbofan upstream wind tunnel