Three-dimensional inviscid flow about supersonic blunt cones at angle of attack.

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."Contract no. 48-4014."Includes bibliographical references (page 16).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.Mode of access: Internet