Heat transfer from hypersonic turbulent flow at a wedge compression corner

Coleman, G. T.; Stollery, J. L.

doi:10.1017/s0022112072002630

Cited by 94 publications

(37 citation statements)

References 2 publications

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“…10͑a͒ is due entirely to changes in p 3 . Dissociation in region 3 causes a lower pressure and hence a reduction in L sep , by as much as 50% at H 0 ϱ ϭ1.…”

Section: ͑35͒mentioning

confidence: 97%

Separation length in high-enthalpy shock/boundary-layer interaction

Davis

Sturtevant

2000

Physics of Fluids

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Experiments were performed in the T5 Hypervelocity Shock Tunnel to investigate nonequilibrium real-gas effects on separation length using a double-wedge geometry and nitrogen test gas. Local external flow conditions were estimated by computing the inviscid nonequilibrium flow field. A new scaling parameter was developed to approximately account for wall temperature effects on separation length for a laminar nonreacting boundary layer and arbitrary viscosity law. A classification was introduced to divide mechanisms for real-gas effects into those acting internal and external to viscous regions of the flow. Internal mechanisms were further subdivided into those arising upstream and downstream of separation. Analysis based on the ideal dissociating gas model and a scaling law for separation length of a nonreacting boundary layer showed that external mechanisms due to dissociation may decrease separation length at low incidence but depend on the free-stream dissociation at high incidence. A limited numerical study of reacting boundary layers showed that internal mechanisms due to recombination occurring in the boundary layer upstream of separation cause a slight decrease in separation length relative to a nonreacting boundary layer with the same external conditions. Correlations were obtained of experimentally measured separation length using local external flow parameters computed for reacting flow, which scales out external mechanisms but not internal mechanisms. These showed the importance of the new scaling parameter in high-enthalpy flows, a linear relationship between separation length and reattachment pressure ratio, and a Reynolds-number effect for transitional interactions. A significant increase in scaled separation length was observed in the experimental data at high enthalpy. The increase was attributed to an internal mechanism arising from recombination in the free-shear layer downstream of separation, perhaps altering its velocity profile. This real-gas effect depends on the combined presence of free-stream dissociation and a cold wall.

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“…10͑a͒ is due entirely to changes in p 3 . Dissociation in region 3 causes a lower pressure and hence a reduction in L sep , by as much as 50% at H 0 ϱ ϭ1.…”

Section: ͑35͒mentioning

confidence: 97%

Separation length in high-enthalpy shock/boundary-layer interaction

Davis

Sturtevant

2000

Physics of Fluids

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“…Assuming that the oil-dot result for the 20 flare case is true, the experimental value of incipient separation is approximately 18 , and the computational value of incipient separation is approximately 13 . This contradicts the findings of Kuehn,8) Coleman 14,16) and Elfstrom 15) who found higher incipient separation angles. This is because the determination of incipient separation is very sensitive to the detection method employed.…”

Section: Turbulent Boundary Layer Studiesmentioning

confidence: 57%

“…This is one of the most significant differences between laminar and turbulent flow. Various researchers 1,8,[14][15][16] have found that very high incipient separation angles (¼ $ 30 ) are possible in hypersonic flow under turbulent conditions. A collection of incipient separation data is shown in Fig.…”

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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“…As a further check, and noting the potential influence of the bow shock for blunt ramps (θ > θ D ), the pressure to heat transfer relation from Coleman and Stollery (1972) is evaluated at the stagnation pressure behind a normal shock, P o,N . Defining the ratios with respect to undisturbed flow conditions, P o,R = P o,N /p u and Q max,R = q ′ max /q u , and through Reynolds analogy:…”

Section: Stagnation Heatingmentioning

confidence: 99%

“…Noting that heat transfer measurements on SBLIs are relatively limited, a selection of pertinent experimental studies for numerical validation purposes was recently carried out by Marvin et al (2013) under the framework of fundamental hypersonics and reentry work. Different forms of canonical SBLIs included: two-dimensional (2D) ramp interactions at Mach 8.2, 9.2 and 11.3 (Coleman and Stollery 1972;Holden 2014)…”

Section: Introductionmentioning

confidence: 99%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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Heat transfer from hypersonic turbulent flow at a wedge compression corner

Cited by 94 publications

References 2 publications

Separation length in high-enthalpy shock/boundary-layer interaction

Separation length in high-enthalpy shock/boundary-layer interaction

Flare-Control Effectiveness at Hypersonic Speeds

Reattachment heating upstream of short compression ramps in hypersonic flow

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