Program VSAERO Theory Document: A Computer Program for Calculating Nonlinear Aerodynamic Characteristics of Arbitrary Configurations |
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Analysis applied assembled becomes body boundary condition boundary layer Calculated chordwise close column combined Comparison of Calculated component computed configuration Consider constant contribution control point coordinate system corner points defined density described direction distance distribution doublet doublet distribution edge effect element equation evaluated exact expression external Figure flow flow field force formulation four geometry given gradient influence coefficients input internal internal flow iteration jump known matrix mean plane method Model neighbor Neumann normal normal velocity obtained panel K panel method patch perturbation plane present Pressure Distributions problem procedure provides quadrilateral Reference region respectively satisfied separation shows side singularity solution specified streamline Subsection surface symmetry tangent vector thick tion unit upper and lower vector velocity potential VSAERO program wake panels Wind wing zero