## A comparative study of the nonuniqueness problem of the potential equationNational Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985 - Mathematics - 20 pages |

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34 mesh airfoil surface angle of attack behavior boundary-layerlike cell coefficient for NACA computed values Computed with FLO conservative potential conservative unknown constraint coordinate damping term described in reference differential equation entropy and velocity erence Euler calcu Euler code evaluated exact jump extrapolated from computed far-field boundary condition far-field vortex figure 16 flow field flow past free-stream Mach number ghost point inside the airfoil inviscid flow isentropic solution isomach Jmax Kutta condition last ring Lift curve obtained mesh refinement modified multiple solutions NACA 0012 airfoil nonconservative potential code nonuniqueness occurs nonuniqueness problem Number of iterations obtained with FLO past an NACA potential code described potential code FLO potential theory Pressure coefficient residual of Cm results presented satisfied the Kutta Shock jump shock wave shown in figure subcritical supercritical speeds surface pressure thinner airfoil tions trailing edge transonic similarity parameter valid velocity components tangent x 34 mesh x-Momentum zero angle