"A two-dimensional numerical study of the effects of a forward-facing supersonic air jet located at the stagnation point of a cylinder-wedge body on wave drag, heat transfer, and skin friction drag is presented for Mach 6.5 free stream flow at 30 km altitude. Jet exit area and jet Mach number are varied parametrically. The full Navier- Stokes equations are used with variable viscosity and variable thermal conductivity. The 2-D version of the FORTRAN code SPARK is used for all solutions. A detailed analysis of time and grid convergence is provided. It is shown that upstream injection can significantly modify the flow field. If the jet conditions are chosen properly, large reductions in drag and heat transfer can be obtained resulting in possible increases in the volumetric efficiency and static stability of aircraft as well as reductions in the heating protection requirements for hypersonic vehicles"--Abstract, page iv.
Nelson, Harlan F., 1938-2005
Riggins, David W.
Isaac, Kakkattukuzhy M.
Bohner, Martin, 1966-
Mechanical and Aerospace Engineering
M.S. in Aerospace Engineering
University of Missouri--Rolla
xi, 107 pages
© 2000 Benjamin Michael Meyer, All rights reserved.
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Meyer, Benjamin Michael, "Numerical investigation of hypersonic drag and heat transfer using a forward facing jet" (2000). Masters Theses. 1926.
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