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W. Anderson, James Thomas, B. Leer (1985)
Comparison of Finite Volume Flux Vector Splittings for the Euler EquationsAIAA Journal, 24
V.V. Zatoloka (1983)
Numerical and experimental research of new configurations of convergent inlets with three-dimensional combinations of flows
V.V. Zatoloka (1976)
On a class of convergent inlets with flat walls and swept leading and trailing edges of inlets
Experimental research of three-dimensional inlets intended for high supersonic flight speeds. Preprint of the ITAM SB of the USSR Acad. Sci. M.A. Goldfeld (1992)
M.A. Goldfeld, Experimental research of three-dimensional inlets intended for high supersonic flight speeds. Preprint of the ITAM SB of the USSR Acad. Sci., Novosibirsk, 1992, No. 13-92.
A.M. Kharitonov Goonko Yu.P. (2000)
Europ. Congr. Computational Methods in Applied Science and Engng. Barcelona
V.V. Zatoloka Yu.P. Goonko (1978)
Research in Hypersonic Aerodynamics
H. Yee, R. Warming, A. Harten (1983)
Implicit Total Variation Diminishing (TVD) schemes for steady-state calculations. [in gas dynamics
A marching procedure of numerical solution of two-dimensional and three-dimensional steady Euler equations using shock-capturing schemes A.N. Kudryavtsev and R.D. Rakhimov (1998)
Proc. Inter. Conf. on the Methods of Aerophysical Research
B. Einfeldt, C. Munz, P. Roe, B. Sjögreen (1991)
On Godunov-type methods near low densitiesJournal of Computational Physics, 92
Convergent inlets with the initial shock wave and additional external compression B.I. Gutov and V.V. Zatoloka (1973)
Aerophysical Research
V.V. Zatoloka B.I. Gutov (1975)
Questions of Gas Dynamics
B.I. Gutov (1993)
Gasdynamic Design of Supersonic Inlets
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.
Thermophysics and Aeromechanics – Springer Journals
Published: Mar 1, 2011
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