Three-dimensional Inviscid Flow about Supersonic Blunt Cones at Angle of Attack: Improved time-dependent techniques for the blunt-body problem. II, Part 2

G. Moretti

1968년 1월 · Sandia Corporation

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Comparisons are made between the cylindrical and polar coordinate system used in determining the three-dimensional shock layer flow over the nose region of a blunted supersonic vehicle. Jusfification for the development of a polar coordinate system is given and an outline for such development is presented. Results from the polar coordinate system are given as is the limiting useful range.