Shock-Wave-Boundary-Layer Interaction Effects on Aerodynamic Heating

Hung, F. T.; Greenschlag, S. N.; Scottoline, C.

doi:10.2514/3.57157

Cited by 17 publications

(7 citation statements)

References 4 publications

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“…9 we have compared the results of investigating the heat transfer on a sharp plate with the experimental data published in [11]. In that study (see also [21]) the results of 11 investigations over a wide range of the M number (from 2.4 to 13), a single Reynolds number (from 1.3 · 10 6 to 1.2 · 10 8 1/m) and the shock generator angles (from 10 • to 20 • were analyzed, the data being obtained both in the laminar and turbulent states of the undisturbed boundary layer.…”

Section: Effect Of Various Factors On Heat Exchange In the Interferenmentioning

confidence: 99%

“…In that study (see also [21]) the results of 11 investigations over a wide range of the M number (from 2.4 to 13), a single Reynolds number (from 1.3 · 10 6 to 1.2 · 10 8 1/m) and the shock generator angles (from 10 • to 20 • were analyzed, the data being obtained both in the laminar and turbulent states of the undisturbed boundary layer. In [11] the quantities St * and Re * , introduced by Ekkert, were used to represent the experimental data. In these quantities the values of the density and viscosity calculated at the determining temperature T *…”

Section: Effect Of Various Factors On Heat Exchange In the Interferenmentioning

confidence: 99%

“…The same formula was also used in [11] to represent the maximum heat transfer coefficient in the interference zone for transition and turbulent flows, the values of the gas density and temperature being calculated behind the impinging and reflected shocks, while the length X is the distance from the leading edge of the plate to the shock impingement point. For this representation many experimental data in [11] are located between the values of the St number given by formula (4.1) and double those values.…”

Section: Effect Of Various Factors On Heat Exchange In the Interferenmentioning

confidence: 99%

“…At the end of the fifties the detailed research into this phenomenon had been begun and this research has continued ever since. Initially, two-dimensional flows were frequently investigated [1][2][3][4][5][6][7][8][9][10][11]. The interaction between a boundary layer and an inclined shock impinging from outside and shocks formed in a compression corner and ahead of a step was considered.…”

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Interaction between an Inclined Shock and Boundary and High-Entropy Layers on a Flat Plate

Borovoi¹,

Егоров²,

Skuratov³

et al. 2005

Fluid Dyn

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The flow structure and heat exchange in the zone of interference between an inclined shock and the surface of a flat plate are investigated experimentally and theoretically as functions of many parameters, the interference being studied in both the presence and the absence of bluntness of the leading edge. The experiments were carried out at Mach numbers M = 6, 8, and 10 and the Reynolds numbers Re L , calculated using the plate length L = 120 mm and the free-stream parameters, varied over the range from 0.24 · 10 6 to 1.31 · 10 6 . The bluntness radius of the leading edge of the plate, the intensity of the impinging shock, and its location with respect to the leading edge were varied. The numerical simulation was carried out by solving the complete two-dimensional Navier-Stokes equations and averaged Reynolds equations using the q-ω turbulence model. The laminar boundary layer became turbulent inside the separation zone induced by the shock. It is shown that the plate bluntness significantly reduces the heat exchange intensity in the interference zone, this effect intensifying with increase in the Mach number.

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Section: Effect Of Various Factors On Heat Exchange In the Interferenmentioning

confidence: 99%

Section: Effect Of Various Factors On Heat Exchange In the Interferenmentioning

confidence: 99%

Section: Effect Of Various Factors On Heat Exchange In the Interferenmentioning

confidence: 99%

mentioning

confidence: 99%

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Interaction between an Inclined Shock and Boundary and High-Entropy Layers on a Flat Plate

Borovoi¹,

Егоров²,

Skuratov³

et al. 2005

Fluid Dyn

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“…Laminar-turbulent boundary layer transition is a pivotal factor for the design of vehicles traveling at hypersonic speeds but the mechanisms that induce transition are not so well understood [1][2][3][4][5]. The primary purpose of this research is to develop a reliable calibrated instrument to assist the study of boundary layer instabilitywave growth at the Purdue Mach-6 wind tunnel.…”

Section: Purposementioning

confidence: 99%

Oscillations in a Forward-Facing Cavity Measured Using Laser-Differential Interferometry in a Hypersonic Quiet Tunnel

Segura¹

2007

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AFOSR/NAUnclassified and Approved for Public Release M.S. thesis by Rodrigo Segura with development of LDI for Mach-6 quiet tunnel and measurements in Mach-4 quiet tunnel Laminar-turbulent transition is a pivotal factor for the design of hypersonic vehicles but the mechanisms that induce transition are not well understood. A laser differential interferometer (LDI) is a non-intrusive optical device that measures the optical path length difference between two laser beams. The LDI is a reliable calibrated instrument to assist the study of boundary layer instability-wave growth in hypersonic flow and has high sensitivity and frequency response. An LDI with a commercial balanced photodetector capable of detecting optical path length differences of lambda/21,000 from DC to 80 MHz was assembled and tested in the Purdue Quiet-Flow Ludwieg tube. Fluctuations in the subsonic region of a forward-facing cavity were measured with the LDI and compared to those detected with a Kulite pressure transducer at the base of the cavity. Predictions of self-resonating deep cavities were confirmed. The LDI was then adapted and transferred to the Boeing/AFOSR Mach-6 Quiet Tunnel. to give special thanks to Joan Jackson; she made me laugh and was patient and helpful even when I demanded her help on rather short notice. Joe Kline's technical assistance is appreciated.A great deal of contribution came from my fellow researchers.

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