Hypersonic Drag and Heat-Transfer Reduction Using a Forward-Facing Jet
A two-dimensional numerical study of the effects of a forward-facing jet located at the stagnation point of a blunt body on wave drag, heat transfer, and skin-friction drag is presented for Mach 6.5 flow at 30 km altitude. The full Navier-Stokes equations are used with variable viscosity and thermal conductivity. It is shown that upstream injection can significantly modify the flowfield. 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.
B. Meyer et al., "Hypersonic Drag and Heat-Transfer Reduction Using a Forward-Facing Jet," Journal of Aircraft, American Institute of Aeronautics and Astronautics (AIAA), Jan 2001.
The definitive version is available at http://dx.doi.org/10.2514/2.2819
Mechanical and Aerospace Engineering
Article - Journal
© 2001 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.