The effects of surface discontinuities on convective hear transfer in hypersonic flow

Nestler, D. E.

doi:10.2514/6.1985-971

Cited by 14 publications

(10 citation statements)

References 24 publications

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“…1). These interactions are strongly three-dimensional and present similar features to more commonly investigated interactions such as those induced by blunt fins (Jones 1964;Neumann and Hayes 1981), cylindrical obstacles in hypersonic flow (Hung and Patel 1984;Nestler 1985;Tang and Yu 1992;Avallone et al 2015) and other specific protuberances (Neumann and Freeman 2012;Kumar andReddy 2013, 2014), which generally involve the formation of a primary horseshoe vortex upon separation and its interaction with the resulting shock structure as it stretches around the obstacle. This study continues from that in Estruch-Samper et al (2010), where semi-empirical correlations of the average heat transfer in the 'hot spot' region were derived based on common nondimensional terms (Mach, Reynolds and Stanton numbers).…”

Section: 2dmentioning

confidence: 88%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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Section: 2dmentioning

confidence: 88%

Reattachment heating upstream of short compression ramps in hypersonic flow

Estruch-Samper

2016

Exp Fluids

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“…The total uncertainty in the parameter F is given by the square root of the sum of squares of each oF¡ (4) For directly measured quantities, such as heat transfer rate, q, the total uncertainty is obtained by the accumulation of its sensitivity to parameters like: (a) error in determination of the temperature co-efficient of resistance of the platinum thin-film gauge, ares. (b) error in measurement of gauge backing matedal properties, (c) error in measurement of initial voltage set for each gauge, (d) error in output of the data acquisition system, and (e) error in amplification factor used in the measurement system.…”

Section: Uncertainty Analysismentioning

confidence: 99%

“…Aerodynamic heating has not been fully characterized for all flow regimes in open literature. Considerable amount of research has been carried out for protuberances which are much larger (about one order or so) compared with the ¿locah but not so much is available on interference heating caused by smaller protrusions with size similar to the oncoming boundary layer thickness [4].…”

Section: Introductionmentioning

confidence: 99%

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

Kumar¹,

Reddy

2013

Journal of Heat Transfer

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Heat transfer rates measured in front and to the side of a protrusion on an aluminum flat plate subjected to hypersonic flow at zero angle of attack are presented for two flow enthalpies of approximately 2 M J/kg and 4.5 M J/kg. Experiments were conducted in the hypersonic shock tunnel (HST2) and free piston driven HST3 at a freestream Mach number of 8. Heat transfer data was obtained for different geometries of the protrusion of a height of 4 mm, which is approximately the local boundary layer thickness. Comparatively high rates of heat transfer were obtained at regions of flow circulation in the separated region, with the hottest spot generally appearing in front of the protuberance. Experimental values showed moderate agreement with existing empirical correlations at higher enthalpy but not at all for the lower enthalpy condition, although the correlations were coined at enthalpy values nearer to the lower value. Schlieren visualization was also done to investigate the flow structures qualitatively.

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“…As part of a larger effort within the shuttle RTF, Everhart et al 2,3 and Wood et al 4 investigated the supersonic/hypersonic cavity flow experimentally and numerically. Especially, they examined the conventionally classified cavity geometry, 5,6,7 where the cavity under the supersonic/hypersonic mainstream is distinguished by using the cavity fundamental parameter: the ratio of length (L) to depth (H). The case of 1≤L/H≤11 is defined as the open cavity, while L/H≥15 is as the closed cavity.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Heating of an Open Cavity in Hypersonic Compression Ramp Flow

Yokoi

Ozawa

Koyama

et al. 2012

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The interaction between the reattachment of laminar boundary layer and an open cavity(L/H=10) in a hypersonic compression ramp was investigated numerically and experimentally. Specifically, the present cavity is placed beneath the boundary layer reattachment in the hypersonic compression ramp. It was found that a high temperature separated shear layer collides with the back wall of cavity, where a hot stagnation point is formed. The maximum heat flux at the present cavity back wall is about 10 times as large as that of the baseline compression ramp without cavity (St=0.180). Even though the present cavity configuration is typical open cavity, the back wall area average heat flux is 2-3 times as large as that of the typical open cavity. The collision pattern between the shaer layer and the back wall is also quite different. The collision of the present cavity is intermittency, while the typical open cavity is continuous. Therefore we concluded that the present cavity placed beneath the boundary layer reattachment produces the quite different heat flux from the typical open cavity's one.

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The effects of surface discontinuities on convective hear transfer in hypersonic flow

Cited by 14 publications

References 24 publications

Reattachment heating upstream of short compression ramps in hypersonic flow

Reattachment heating upstream of short compression ramps in hypersonic flow

Experimental Investigation of Heat Fluxes in the Vicinity of Protuberances on a Flat Plate at Hypersonic Speeds

Aerodynamic Heating of an Open Cavity in Hypersonic Compression Ramp Flow

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