## Application of the Inverse Technique to the Flow Over a Blunt Body at Angle of Attack, Volume 445 |

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AIAA angle of attack arc length axis ratio Blunt Bodies bodies at angle body shape bow shock shape Cartesian coordinates CATENARY SHOCK WAVE contain partial derivatives coordinate system Cornell Aeronautical Laboratory cylindrical coordinates define the data derivatives with respect directional derivatives discussed dp P ds flow conservation equations flow field flow variables Flux entering freestream velocity vector highly nonaxisymmetric Hypersonic ideal gas initial conditions initial data points initial values integration ray integration steps integration surface inverse method inverse technique Inviscid mass flux nonaxisymmetric bodies nonaxisymmetric shock nondimensional Nonequilibrium Flow numerical derivatives numerical integration particular data point plane of constant plane of symmetry point defined present program reduced flow conservation Rept respect to arc shock shape chosen shock surface shown in Fig smoothing subscript Supersonic Flow total derivatives trace defined traces of constant traces which intersect unit area unknown partial derivatives x-axis x-z plane