Hypersonic Viscous Flows

Henderson, Arthur

doi:10.1007/978-1-4615-8624-1_3

Cited by 6 publications

(3 citation statements)

References 30 publications

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“…Allowing for the lower Mach number in the model shock layer* 22 ', these results are consistent with the presence of a smooth model surface. Miller* 23 ) reports shock layer transition Reynolds numbers, on a similar model, of approximately 2-3xl0 6 in a conventional hypersonic wind tunnel.…”

Section: Effect Of Reynolds Number -Transitionsupporting

confidence: 75%

Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

Krek

Stalker

1992

Aeronaut. j.

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Heat transfer and pressure measurements were made on a model of the United States Space Shuttle Orbiter in the University of Queensland's T4 shock tunnel at three angles of attack, with stagnation enthalpies which varied by a factor of 11, from 2·1 MJ/kg to 23 MJ/kg and normal shock Reynolds numbers which varied by a factor of 38, from 2·1 x l04 to 8·l x 105. Leeward pressure results were obtained for comparison with flight data and equilibrium calculations, but the majority of the experiments were conducted to investigate the heat transfer distributions around the shuttle model. Both the windward and leeward heat transfer results exhibit the onset of transition to turbulent flow. The leeward results are compared with flight data as well as with conventional wind tunnel data, and are used to establish trends associated with variation in the major flow and geometry parameters. It was found that although high enthalpy effects could be important, Reynolds number effects played a dominant role in determining the flow.

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Section: Effect Of Reynolds Number -Transitionsupporting

confidence: 75%

Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

Krek

Stalker

1992

Aeronaut. j.

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“…The hypersonic viscous interaction problem was intensively studied in the nineteen-fifties and sixties [3][4][5] and later [6,7]. It was established that for strong interaction (for large values of the viscous interaction parameter χ 1) both the pressure on the plate surface and the heat transfer coefficient increase significantly.…”

mentioning

confidence: 99%

“…In [8] the results of experiments carried out in air at Mach and Reynolds numbers M = 12 and Re L from 0.6 · 10 5 to 0.6 · 10 6 , which are in agreement with the theoretical results, were presented. In [5] experimental data obtained mainly in helium for Mach numbers up to 41.4 were given.…”

mentioning

confidence: 99%

Laminar heat exchange on sharp and blunt plates in a hypersonic air flow

Borovoi¹,

Егоров²,

Skuratov³

et al. 2005

Fluid Dyn

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The results of an experimental investigation and numerical simulation of heat exchange are given for sharp and blunt plates in a hypersonic air flow. The experiments were carried out in a Ludwig-type wind tunnel at hypersonic Mach numbers and a Reynolds number Re L which varied over the range from 0.24 · 10 6 to 1.31 · 10 6 . The bluntness radius r was varied over the range from 0.008 mm (almost sharp plate) to 4 mm (the corresponding Reynolds numbers Re r from 15 to 4 · 10 4 ). The numerical simulation was carried out by solving the complete two-dimensional Navier-Stokes equations. The experimental data were correlated using the well-known viscous hypersonic interaction parameters.

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Efficiency of the invariant gradient criterion of stability for the flight conditions of the flow around axisymmetric bodies in the early stage of transition and relaminarization

Гапонов¹,

Pavlyuchenko²,

Popkov³

1999

J Appl Mech Tech Phys

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Quantitative results of the study of the invariant gradient criterion of stability, which was theoretically obtained by N. N. Yanenko and S. A. Gaponov, for Introduction and Formulation of the Problems. To obtain reliable data on the thermal state of supersonic and hypersonic aircraft and their drag and dynamics, it is necessary to have credible results on the Reynolds numbers of the laminar-turbulent transition and relaminarization (reverse transition) in supersonic and hypersonic near-wall boundary layers. The problems of stability and transition to turbulence in incompressible and compressible laminar near-wall flows and relarninarization of turbulent boundary layers are rated among the most complicated problems in continuum mechanics. Their importance and practical interest are emphasized [1][2][3][4][5]. Despite the great number of theoretical papers, which are reviewed, for example, in [2, [4][5][6], there is no comprehensive theory of the transition of the laminar boundary-layer flow to a turbulent state. In connection with the use of effective numerical methods, techniques based on the theory of hydrodynamic stability, both linear [2, 4, 7, 8] and nonlinear [9-13], have been developed. Taking into account the difficulties of theoretical investigation of the transition in near-wall boundary layers and its practical importance, Yanenko and Gaponov [14] noted that it is important to determine the conditions of stability and transition on the basis of local flowfield properties.It is impossible now to obtain reliable data on the transition in supersonic wind tunnels, first of all, because of the presence of an acoustic field in test sections [15, 16]. It is shown [17, 18] that the transition Reynolds numbers on the cones which were measured in flight were many-fold higher than those measured in wind tunnels. Along with the acoustic field, scaling effects make an additional contribution to the difference in ground-based and flight data on the laminar-turbulent transition for Moo >/2.0. These effects are caused by the fact that the full-scale Reynolds and Mach numbers and the temperature factor, the external flow perturbations, the effect of operating engines, and the aeroelastic properties of the bodies cannot be simultaneously simulated in supersonic and hypersonic wind tunnels. Reshotko [1] emphasized the necessity of careful preparation of flight experiments for studying the laminar-turbulent transition. The number of experiments conducted is rather small [17][18][19][20][21]. For example, a full-scale experiment was conducted at the Institute of Theoretical and Applied Mechanics (ITAM) of the Siberian Division of the Russian Academy of Sciences on the aerophysical complex "Oblako" ("Cloud") with a working engine [22]. The results obtained are in good agreement with the in-flight data of NASA [18] for free flying cones for identical Reynolds (Rel,oo) and Mach (Moo) numbers. However, the operating engines on the "Oblako" affected the transition for some Reynolds and Mach numbers.

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Hypersonic Viscous Flows

Cited by 6 publications

References 30 publications

Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

Experiments on Space Shuttle Orbiter models in a free piston shock tunnel

Laminar heat exchange on sharp and blunt plates in a hypersonic air flow

Efficiency of the invariant gradient criterion of stability for the flight conditions of the flow around axisymmetric bodies in the early stage of transition and relaminarization

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