A compressible solution of the Navier-Stokes equations for turbulent flow about an airfoil
S. J. Shamroth, H. J. Gibeling, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, Langley Research Center
National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1979 - Mathematics - 63 pages
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adverse pressure gradient AIAA airfoil at zero airfoil flow field airfoil leading edge airfoil surface analysis applied approach approximately boundary conditions boundary layer Briley and McDonald Briley Ref candidate form Cartesian coordinates Cartesian velocity centerline Coefficient in tensor compressible computed constructive coordinate system coordinate direction coordinate line cylinder density dependent variables derivatives difference equations Douglas-Gunn Dynamic Stall Eiseman Ref form of momentum formulation Gibeling governing equations Gregory and O'Reilly grid points grid resolution Helicopter Rotor implicit difference incompressible inviscid kinetic energy equation leading edge region linearized block implicit Mach number McDonald Ref method metric tensor momentum equation NACA 0012 airfoil Navier-Stokes equations nonlinear nonorthogonal O'Reilly Ref obtained partial differential equations Poisson's equation predicted present effort pressure distribution pressure surface Reynolds number Shamroth and Eiseman solution procedure spatial suction surface tensor form turbulence energy turbulence kinetic energy turbulence model turbulent flow turbulent viscosity Unsteady Aerodynamics velocity components zero incidence