The expansion of a hypersonic turbulent boundary layer at a sharp corner

Bloy, A. W.

doi:10.1017/s0022112075000523

Cited by 12 publications

(6 citation statements)

References 8 publications

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“…Next, Fig. 6 compares the present theoretical results for hypersonic, turbulent flow past 5-, 10-, and 15-deg expansion corners against Bloy's experimental data, 8 with the following conditions: T w = 280 K, T 0 = 2160 K, M^ = 7.35, and Re = 29 x 10 6 /m. In the first case, Eq.…”

Section: Application and Discussionmentioning

confidence: 88%

“…(4), and the coupling equation, Eq. (8). The solution is started once the initially unknown pressure P in Eq.…”

Section: Application and Discussionmentioning

confidence: 99%

“…5 (7) can be differentiated with respect to x to yield d8* dx -+ dx dx (8) from which K v -M^ dy e /dx can be evaluated. It may be noted here that Eq.…”

Section: Brief Review Of Turbulent Viscous Interaction Theorymentioning

confidence: 99%

“…(12) and (13) incorporate the weak and strong approximations to the tangent-wedge rule as given by Stollery and Bates. 5 The last term in these equations describes the joint effects of viscous interaction and incidence through the weak viscous interaction parameter % w and the parameter K. The power of % w , -0.4 and 0.4 in the respective equations, is empirically determined through comparisons with experimental data, 8 " 10 and such comparisons will be discussed later. It is found that for strong expansions where K > 1, the negative power of % w in Eq.…”

Section: Pressure Law For Expansion Cornersmentioning

confidence: 99%

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Hypersonic, turbulent viscous interaction past an expansion corner

Bigdeli

1994

AIAA Journal

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Turbulent, viscous interaction theory is used to understand the hypersonic flow past an expansion corner. By assuming a pressure law, the boundary-layer properties of the flow are obtained through simultaneous solution of a displacement thickness relationship and a coupling equation relating the effects of incidence and displacement thickness to the effective body shape. The pressure law is obtained through examination of available experimental data. The form of the pressure law is found to depend on the incidence. The pressure decay is dependent on both viscous and incidence effects. For weak incidence, viscous effects are important throughout the interaction, and they produce a gentle pressure decay. For strong incidence, viscous effects are important only near the front of the corner. In this latter case, the pressure decays rapidly followed by a long asymptotic downstream region; the overall pressure distribution then appears more similar to the in viscid case. NomenclatureA B C^ = constant of proportionality in linear viscosity-temperature relationship K -hypersonic similarity parameter, M^cc K v = modified hypersonic similarity parameter, M^ dy e (x)/ dx M = Mach number P(x) = nondimensional pressure, p^/pp = pressure Re = unit Reynolds number T = temperature U = velocity (x, y) = physical coordinates along and normal to the incoming flow a = expansion corner angle y = ratio of specific heats 8 = boundary-layer thickness 6* = boundary-layer displacement thicknesŝ = dummy variable of integration p = density % = weak turbulent, viscous interaction parameter, (M 9 C / Re*) 115 Subscripts e = edge condition or effective w = wall condition oo = incoming freestream condition 0 -stagnation condition

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Section: Application and Discussionmentioning

confidence: 88%

“…(4), and the coupling equation, Eq. (8). The solution is started once the initially unknown pressure P in Eq.…”

Section: Application and Discussionmentioning

confidence: 99%

“…5 (7) can be differentiated with respect to x to yield d8* dx -+ dx dx (8) from which K v -M^ dy e /dx can be evaluated. It may be noted here that Eq.…”

Section: Brief Review Of Turbulent Viscous Interaction Theorymentioning

confidence: 99%

Section: Pressure Law For Expansion Cornersmentioning

confidence: 99%

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Hypersonic, turbulent viscous interaction past an expansion corner

Bigdeli

1994

AIAA Journal

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“…However, in 1969 he had moved to Imperial College, London, where he obtained his doctorate before joining the Von Kármán Institute (VKI), Belgium, to continue his doctoral work on hypersonic aerodynamics. Soon after his arrival in Manchester he published his results (228) for heat transfer and surface pressures on a sharp wedge expansion flap tested at Mach 16 in the VKI's Longshot tunnel. Later he too joined the Department's jet programme, showing by characteristics calculations that temperature perturbations at a nozzle's inlet can cause significantly large pressure disturbances resulting in excess noise (229) .…”

Section: The Department Of the Mechanics Of Fluids And Its Successorsmentioning

confidence: 99%

The Victoria University of Manchester’s contributions to the development of aeronautics

Ackroyd

2007

Aeronaut. j.

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This issue of the Aeronautical Journal celebrates the 50th anniversary of the foundation of the Honours Degree Course in Aeronautical Engineering at the Victoria University of Manchester. The following article therefore describes the aeronautical research and teaching activities of that university up to its recent amalgamation with the University of Manchester Institute of Science and Technology (UMIST) to form the present-day University of Manchester. This juncture provides a further justification for recording the Victoria University’s achievements.Both the Victoria University and UMIST had their roots in the nineteenth century although, apart from the relatively brief period of the First World War, neither of them was particularly involved in aeronautics until after the Second World War. However, as Sections 6.0-10.0 seek to demonstrate, thereafter the Victoria University’s involvement became considerable. The preceding Sections describe the origins of the Victoria University and UMIST and, in the case of the former institution, the subsequent activities of its staff and graduates in engineering and mathematics which, although not always specifically aeronautical in content, nonetheless had a profound influence on the development of the aeronautical sciences.

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Interaction of second-mode wave packets with an axisymmetric expansion corner

Butler

Laurence

2021

Exp Fluids

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The expansion of a hypersonic turbulent boundary layer at a sharp corner

Cited by 12 publications

References 8 publications

Hypersonic, turbulent viscous interaction past an expansion corner

Hypersonic, turbulent viscous interaction past an expansion corner

The Victoria University of Manchester’s contributions to the development of aeronautics

Interaction of second-mode wave packets with an axisymmetric expansion corner

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