Supersonic flow past a family of blunt axisymmetric bodies
Milton Van Dyke, Helen D. Gordon, Ames Research Center, United States. National Aeronautics and Space Administration
U.S. G.P.O., 1959 - Science - 25 pages
Some 100 numerical computations have been carried out for unyawed bodies of revolution with detached bow waves. The gas is assumed perfect with y=5/3, 7/5, or 1. Free-stream Mach numbers are taken as 1.2, 1.5, 2, 3, 4, 6, 10, and [infinity symbol]. The results are summarized with emphasis on the sphere and paraboloid.
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accuracy adiabatic exponent axis of symmetry axisym becomes negative BLUNT AXISYMMETRIC BODIES blunt bodies blunter Body n x/R body shape calculated conic section curvilinear coordinate DATA FOR SPHERES Detached Shock Wave division by zero downstream ellipsoid end instability equation 13a equations of motion Exact externally iterated Figure 15(a free-stream Mach number high Mach numbers Hypersonic infinite Mach number IV.—GEOMETRY AND PRESSURE Jour line Body x/R Mach wave method of characteristics number of points numerical procedure orthogonal coordinate outermost points plane flow PRESSURE DATA pv/p round-off error scheme Shock Sonic line Shock x/R shown in figure SOLUTION FOR SPHERE Sonic line Body Sonic line x/R sonic point sphere and paraboloid Sphere at M=2 SPHERES AND PARABOLOIDS—Continued stagnation point stand-off distance step stream function SUPERSONIC FLOW PAST surface pres TABLE IV.—GEOMETRY Taylor series tion value of 77 values from supplementary wave and body zero in computing