Turbulent hypersonic viscous interaction

Stollery, J. L.; Bates, L.

doi:10.1017/s0022112074001054

Cited by 35 publications

(38 citation statements)

References 7 publications

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“…They compared their theory with experimental data obtained by Coleman and Stollery 6 and Elfstrom. 7 The present paper extends the turbulent, viscous interaction theory 5 to the case of expansion corners (Fig. 1) in a straightforward way.…”

Section: Introductionmentioning

confidence: 61%

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: Introductionmentioning

confidence: 61%

Hypersonic, turbulent viscous interaction past an expansion corner

Bigdeli

1994

AIAA Journal

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“…The hypersonic similarity parameter K = Mθ is experimentally validated for both hypersonic compression and expansion problems (Stollery and Bates 1974), yet at significantly lower angles than those considered here. As per Fig. 14, the present dependence on θ for angles well in excess of the inviscid detached shock condition suggests that the increasing extent of the separation is driven by the influence of the expansion of the flow at the trailing edge of the compression surface, i.e.…”

Section: Effect Of Deflection Anglementioning

confidence: 86%

“…Eventually, the competing effect between the 'strong inviscid term' (M o θ) 2 and the 'strong displacement term' χ s leads to a much weaker influence of Reynolds and Mach number in contrast to that of deflection angle (Stollery and Bates 1974). As interpreted in Fig.…”

Section: Effect Of Deflection Anglementioning

confidence: 91%

“…For turbulent flow, and with reference to local flow conditions, Stollery and Bates (1974) define: Settles and Bogdonoff (1982), the exponential increase in separation length with deflection angle is well established to scale proportionally with mass flow deficit ratio across the interaction (Souverein et al 2013) and is thus to some extent sensitive to the fraction of low momentum flow bled to the sides of the obstacle (and hence width).…”

Section: Effect Of Deflection Anglementioning

confidence: 99%

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Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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“…Since turbulent separated flow is unsteady, most measurements in Fig. 1 17) have suggested that by analogy to the laminar case:…”

Section: Turbulent Interactionsmentioning

confidence: 99%

Flare-Control Effectiveness at Hypersonic Speeds

Kontis

2004

Trans. Japan Soc. Aero. S Sci.

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The effects of flare control on the aerodynamic characteristics, performance, and stability of a cylindrical body under laminar and turbulent boundary layer conditions have been studied experimentally and computationally. The experimental study has been carried out in a hypersonic gun tunnel at a Mach number of 8.2 and a Reynolds number of 158,100, based on the cylinder diameter, at flare angles 0, 5, 10, 15, 20, 25 and 30 degrees and at pitch angles of À12 to 12 deg for the 10 deg flare case only. The surface flow was studied using the oil-dot technique. Some information regarding the shock layer was obtained from schlieren pictures. The effects of turbulence on onset of separation were also deduced from pressure measurements over the cylinder and the flare. The forces were measured with a three-component balance equipped with semiconductor strain gauges. The effects of centre of gravity (CG) location on the aerodynamic characteristics and in particular on the C M were examined. The results under turbulent conditions and zero-incidence were compared with numerical simulations performed using a 3-D time-marching Navier-Stokes code. The magnitude of the separated region, the minimum flare angle required to induce separation, and the effects of small-scale separation are detailed.

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Turbulent hypersonic viscous interaction

Cited by 35 publications

References 7 publications

Hypersonic, turbulent viscous interaction past an expansion corner

Hypersonic, turbulent viscous interaction past an expansion corner

Reattachment heating upstream of short compression ramps in hypersonic flow

Flare-Control Effectiveness at Hypersonic Speeds

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