Abstract
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 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 and reductions in heating protection requirements for hypersonic vehicles.
Recommended Citation
B. Meyer et al., "Hypersonic Drag and Heat Transfer Reduction using a Forward Facing Jet," 9th International Space Planes and Hypersonic Systems and Technologies Conference, American Institute of Aeronautics and Astronautics, Jan 1999.
The definitive version is available at https://doi.org/10.2514/6.1999-4880
Department(s)
Mechanical and Aerospace Engineering
Publication Status
Full Access
Document Type
Article - Conference proceedings
Document Version
Citation
File Type
text
Language(s)
English
Rights
© 2024 American Institute of Aeronautics and Astronautics, All rights reserved.
Publication Date
01 Jan 1999
