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Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow

Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow Abstract The design of supersonic three-dimensional inlets using the V-shaped body forming a two-dimensional flow including an initial oblique shock wave and a subsequent isentropic compression wave is considered. Such a flow appears attractive for inlets design due to a possibility of obtaining high compression levels of external flow over the inlet ramp with small losses of the total pressure. Numerical computations of the flows around the designed configurations were carried out in design and off-design regimes using Euler code. The flow structure was identified, the aerodynamic characteristics of the inlets were determined. The investigation covers the range of supersonic speeds corresponding to the freestream Mach numbers M∞= 1.8−2.5. http://www.deepdyve.com/assets/images/DeepDyve-Logo-lg.png Thermophysics and Aeromechanics Springer Journals

Design of supersonic three-dimensional inlets using two-dimensional isentropic compression flow

Thermophysics and Aeromechanics , Volume 18 (1): 14 – Mar 1, 2011

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References (12)

Publisher
Springer Journals
Copyright
2011 Pleiades Publishing, Ltd.
ISSN
0869-8643
eISSN
1531-8699
DOI
10.1134/S0869864311010100
Publisher site
See Article on Publisher Site

Abstract

Abstract The design of supersonic three-dimensional inlets using the V-shaped body forming a two-dimensional flow including an initial oblique shock wave and a subsequent isentropic compression wave is considered. Such a flow appears attractive for inlets design due to a possibility of obtaining high compression levels of external flow over the inlet ramp with small losses of the total pressure. Numerical computations of the flows around the designed configurations were carried out in design and off-design regimes using Euler code. The flow structure was identified, the aerodynamic characteristics of the inlets were determined. The investigation covers the range of supersonic speeds corresponding to the freestream Mach numbers M∞= 1.8−2.5.

Journal

Thermophysics and AeromechanicsSpringer Journals

Published: Mar 1, 2011

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