Attenuation of sound in a low Mach number nozzle flow
M. S. Howe, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office
National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979 - Science - 41 pages
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THE FLUX OF ENERGY THROUGH THE NOZZLE
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acoustic field acoustic wavelength ambient medium Appendix area ratio A/A axi-symmetric back-reaction Bj Bechert boundary layer broadband cold jet component convect density dipole downstream energy flux enthalpy essentially incompressible excitation exterior flow exterior fluid exterior jet flow exterior shear flow FA(y finite width shear fluctuating free space radiation Green's function Helmholtz number hydrodynamic attenuation hydrodynamic end-correction incident wave 2.2 incompressible flow incompressible limit incompressible properties instability mode instability waves jet pipe Kutta condition large compared low Mach number Mach number nozzle mean flow mean shear layer MEASURED RATIO Michel and Pfizenmaier Munt nozzle contraction nozzle lip number nozzle flow obtained perturbation velocity Pfizenmaier 1977 Pinker and Bryce potential region power flux predicted reflection coefficient relative to unity shear layer model shed vorticity small Strouhal number sound speed standing waves subsonic nozzle flow surface integral volume integral vortex sheet model width shear layer