Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flows

Potter, Jan; Whitfield, Jack D.

doi:10.1017/s0022112062000385

Cited by 122 publications

(26 citation statements)

References 7 publications

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“…Trips were made as small disks of 1-millimeter diameter and 0.2-millimeter thick that were placed in 3 rows on the distance from 15 to 25 mm from plate leading edge with the step of 3 mm. Trips height was calculated by A. Skuratov based on [3,4]. Transition delay relative to generators position should be about 50 mm for M = 6 according to this calculation.…”

Section: Experimental Facility and The Modelmentioning

confidence: 99%

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Borovoy

Mosharov

Noev

et al. 2012

Progress in Flight Physics

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Application of Temperature Senstive Paint (TSP) technology for investigation of boundary layer transition in short-duration wind tunnels is presented. Investigations were made on sharp and blunted §at plates in UT-1 wind tunnel of TsAGI operated in Ludwieg scheme at Mach numbers 5, 6, and 8 (Reynolds numbers from 5.5 · 10 6 to 26 · 10 6 ). Both natural and induced boundary layer transitions were investigated. BACKGROUNDTemperature Sensitive Paint method is a very e¨ective optical technique for heat §ux measurements. It provides the pattern of heat transfer rates on the whole visible model surface that is essential for three-dimensional (3D) §ows. In few recent years, this technique is successfully developed in TsAGI for short-duration wind tunnels [1,2].Temperature Sensitive Paint is a specially developed paint containing speci¦c luminophore which luminescence depends on temperature. Being excited by the light of appropriate spectral range, the TSP emits the luminescent light of longer wavelength range, and luminescent light intensity decreases with an increase of temperature. Thus, the temperature distribution can be determined in each point of investigated surface from noncontact optical measurement of TSP luminescence intensity by acquiring an image of the whole investigated surface. But luminescence intensity depends not only on temperature but also on excitation light intensity and TSP thickness. To exclude an e¨ect of excitation light intensity and TSP thickness, it is necessary to acquire second reference image of investigated surface at known temperature. Normalization of active image (acquired at unknown temperature distribution) on reference image exclude an e¨ects of Progress in Flight Physics 3 (2012) 15-24

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Section: Experimental Facility and The Modelmentioning

confidence: 99%

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Borovoy

Mosharov

Noev

et al. 2012

Progress in Flight Physics

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show abstract

“…A comparison of transition detection methods given in Ref. 3 shows that peak temperature recovery factor locations roughly coincide with average transition streamlengths determined from shadowgraphs, that is, S peak ¼ S optical . In addition, quiet-tunnel data from Ref.…”

Section: Analysis and Data Selectionmentioning

confidence: 61%

“…However, results from shadowgraphs generally yield transition locations roughly halfway between onset and end. 3 Transition onset locations can be estimated from optically determined shadowgraph results using information given in Refs. 3 and 4.…”

Section: Analysis and Data Selectionmentioning

confidence: 99%

Algebraic Correlation for High-Speed Transition Prediction on Sphere Cones

Muramoto

2003

Journal of Spacecraft and Rockets

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ENGINEERING NOTES where ¹ 0 is the permittivity of free space. In the constant velocity approximation this magnetic energy is supplied by the Poynting ux:where A is the area across which the plasma ux is supplied. ConclusionsThe rigorous analytical derivation shows that 1=r scaling is consistent with magnetic eld lines "frozen" in a sphericallyexpanding plasma and not just a result of a numerical simulation. The magnetic eld energy is imparted at the source and does not rely on the properties of an interacting solar wind for additional energy. However, the derivation is idealized and still leaves open critical questions concerning the application of M2P2 to real spacecraft propulsion.

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“…Stilling chamber area, ft 2 At Throat area, ft 2 ao Speed of sound in the stilling. chamber, ft/sec b Leading edge thickness, in.…”

Section: Asmentioning

confidence: 99%

A Comparison of Transition Reynolds Numbers From 12-In. And 40-In. Supersonic Tunnels

Schueler¹

1963

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Effects of slight nose bluntness and roughness on boundary-layer transition in supersonic flows

Cited by 122 publications

References 7 publications

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Temperature sensitive paint application for investigation of boundary layer transition in short-duration wind tunnels

Algebraic Correlation for High-Speed Transition Prediction on Sphere Cones

A Comparison of Transition Reynolds Numbers From 12-In. And 40-In. Supersonic Tunnels

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