1965
DOI: 10.2514/3.3316
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Theory of laminar near wake of blunt bodies in hypersonic flow.

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Cited by 92 publications
(8 citation statements)
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“…And in this sense, from the point of view of transition development in the boundary layer-free viscous layer-wake system, the free viscous layer is stable. The data obtained correspond to the statements of Reeves & Lees (1965) that in a viscous free layer (up to the throat of a wake) at M > 3 there is laminar flow. The development of disturbances in the wake (regular wake) is shown in figures 7 and 8, where the spectra of energy of fluctuations, measured in the layer close to the critical one (with the maximum level of disturbances), and in the plane of symmetry of the wake y = 0, are presented (at x = 40, 60, 80 mm and 40, 50, 60 mm).…”
Section: Stability Of the Wake At Mach Number M ∞ =supporting
confidence: 82%
“…And in this sense, from the point of view of transition development in the boundary layer-free viscous layer-wake system, the free viscous layer is stable. The data obtained correspond to the statements of Reeves & Lees (1965) that in a viscous free layer (up to the throat of a wake) at M > 3 there is laminar flow. The development of disturbances in the wake (regular wake) is shown in figures 7 and 8, where the spectra of energy of fluctuations, measured in the layer close to the critical one (with the maximum level of disturbances), and in the plane of symmetry of the wake y = 0, are presented (at x = 40, 60, 80 mm and 40, 50, 60 mm).…”
Section: Stability Of the Wake At Mach Number M ∞ =supporting
confidence: 82%
“…One chooses a trial value of M,; the corresponding value of V, is then obtained from (4.8); the boundary conditions for (4.6) are split between 7 = 0 and 7 = 03. One finds that, for each trial initial value of fq(0) or x, t Reeves & Lees (1965, p. 2094, state that the only similar solution for B compressible free shear layer is for adiabatic flow, in which case the Cohen-Reshotko (1956) equations for non-adiabatic flow reduce to (4.6) above.…”
Section: Numerical Resultsmentioning
confidence: 99%
“…Equation (3.9) is more general: it applies to adiabatic and non-adiabatic flows of arbitrary Prandtl number, and is far simpler than the equivalent expression that emerges from the approximate integral techniques (e.g. compare with equation (3.6) in Reeves & Lees 1965).…”
Section: (I) the Pressure-area Relationmentioning
confidence: 99%
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“…The external flow above the rear stagnation point is not parallel to the axis, and undergoes further compression beyond this point. Reeves and Lees (18) have established that the length over which recompression takes place, and hence the amount of departure from isentropic behaviour, is primarily a function of the free shear layer thickness at the start of recompression. With increasing Re, the efficiency of recompression increases, leading to a higher base pressure, an effect just the opposite of that arising from conservation of angular momentum in the recirculation region.…”
Section: Reynolds Number Effectsmentioning
confidence: 99%