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On a class of convergent inlets with flat walls and swept leading and trailing edges B.I. Gutov and V.V. Zatoloka (1976)
Physical Gas Dynamics
V.V. Zatoloka (1992)
Numerical and experimental investigation of new configurations of convergent inlets with three-dimensional combinations of flows
Yu.P. Goonko (1995)
Gas-dynamic design of aerodynamic configurations with convergent compression surfaces and inlets
A.G. Taryshkin V.P. Starukhin (1982)
Investigation of boundary layer parameters in front of the entrance of a two-dimensional supersonic inlet mounted under a triangular plateUch. zap. TsAGI, 13
G.A. Kisel (1975)
Tests of hypersonic convergent inlet at M = 1.75−6
G.A. Kisel (1975)
Tests of convergent inlet diffuser under the angles of attack 0–12° at the Mach numbers 8, 4, and 11
M.A. Goldfeld (1992)
Experimental investigations of three-dimensional inlets for high flight speeds, Preprint of the ITAM Sib. Branch
Calculation of pressure recovery at transition from supersonic flow to subsonic flow in different systems of plane shock waves G.I. Petrov and E.P. Ukhov (1947)
G.I. Petrov and E.P. Ukhov, Calculation of pressure recovery at transition from supersonic flow to subsonic flow in different systems of plane shock waves, Moscow, 1947.
Patent No. Yu.P. Goonko (2008)
Yu.P. Goonko, Patent No. 2343297 RF, Supersonic inlet. BIPM No. 30, 2008, P. 470.
V.V. Zatoloka (1973)
Convergent inlet diffusers with initial shock wave and additional external compression, in: Aerophysical Research
Yu.N. Yudintsev (1978)
On a class of configurations of hypersonic flying vehicles with convergent inlets designed from three-dimensional combinations of V-shaped bodies
V. Keldysh, G. Maikapar (1969)
Gasdynamic design of hypersonic airplanesFluid Dynamics, 4
Der Druckrueckgewinn bei Geschossen mit Rueckstossantrieb bei hohen Ueberschallgeschwin-digkeiten. Forschungen und Entwicklingen des Heerswaffenamates. Bericht Nr. K. Oswatisch (1005)
Göttingen, January 1944
V.V. Zatoloka (1975)
Tests of the convergent inlet model with the design Mach number 4 in a range of Mach numbers and angles of attack
Aerodynamic Design of Supersonic Inlets V.A. Shchepanovsky and B.I. Gutov (1993)
V.A. Shchepanovsky and B.I. Gutov, Aerodynamic Design of Supersonic Inlets, Nauka, Novosibirsk, 1993.
Abstract The results of designing and numerical gas-dynamic modeling a supersonic three-dimensional inlet of a new type are considered. A ramp of external compression of this inlet is the V-shaped body forming an initial plane oblique shock wave and a subsequent isentropic compression wave. The inlet incorporates an entrance section of internal compression, where also a plane oblique shock wave and a subsequent isentropic compression wave are formed by a cowl. The designed three-dimensional inlet has small inclination angles of compression surfaces, which ensures its low wave drag. According to the estimates of inlet efficiency in terms of the compression ratio and the total pressure recovery factor, it is close to the optimal two-dimensional shocked inlet of external compression considered by Oswatisch as well as Petrov and Ukhov. The flow in the inlet was computed with the use of the Euler and Navier — Stokes codes provided by the commercial package “FLUENT”. The flow in the inlet throat in the design regime computed under the inviscid flow approximation is uniform. The most substantial effect of the flow viscosity in this regime manifests itself in the interaction of the shock wave from the cowl with the boundary layer on the V-shaped compression body in the inlet internal duct. According to computed data, the boundary layer separation does not occur in this case; however, due to viscosity effects, reflected shock waves are formed here which results in significant deviations of flow structure as compared to the computed inviscid flow.
Thermophysics and Aeromechanics – Springer Journals
Published: Mar 1, 2010
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