The method of integral relations has been used to compute the inviscid flow over a blunt body immersed in a nonuniform, expanding flow field. Emphasis has been placed on defining the flow environment experienced by a nose tip model in the exhaust plume of an underexpanded arc jet or rocket engine. Accordingly, the integral method has been formulated for an arbitrary description of a free stream which possesses both axial and radial gradients in Mach No., flow angle, total pressure, and total enthalpy.
The Blunt Body Problem in an Expanding, Nonuniform Flow Field
1970
100 pages
Report
No indication
English
Rocket Engines & Motors , Combustion & Ignition , Fluid Mechanics , Blunt bodies , Inviscid flow , Nose tips , Nonuniform flow , Exhaust plumes , Supersonic nozzles , Flow fields , Expansion , Angles , Gradients , Arc jet engines , Rocket engines , Partial differential equations , Free stream , Pressure distribution , Axial flow , Radial flow , Spheres , Disks , Sizes(Dimensions) , Viscous flow , Expanding flow fields , Underexpanded exhaust plumes , Circular disks , Integral relations , Arc jets , Free jets
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