Reviews of Studies of Boundary Layer Transition in Hypersonic Flows Over Axisymmetric and Elliptic Cones Conducted in the CUBRC Shock Tunnels

Holden, Michael; Wadhams, Timothy; MacLean, Matthew; Mundy, Erik

doi:10.2514/6.2009-782

Cited by 31 publications

(16 citation statements)

References 11 publications

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“…This feature is evident in the turbulent as well as the laminar boundary layer. Generally the transition patterns are similar to those observed for the HIFiRE-5 configuration in the CUBRC LENS I wind tunnel, with the exception of leading-edge transition 27 , as noted in the discussion of the side surface below. It should be noted that the AEDC elliptic cone transition patterns shown in Fig.…”

Section: Windside Heatingsupporting

confidence: 54%

“…In all cases the smooth leading edge transition appears downstream from the centerline transition and appears to result from a smooth merger of the turbulent fields on the top and bottom of the model. This transition pattern is in contrast to a distinct leading-edge-first transition observed in some cases in tests at CUBRC 27 . The cause of this difference in transition behavior between the current tests and CUBRC tests is unclear at this point.…”

Section: Leeside Heatingcontrasting

confidence: 43%

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Aerothermodynamic Characteristics of Boundary Layer Transition and Trip Effectiveness of the HIFiRE Flight 5 Vehicle

Berger

Rufer

Kimmel

et al. 2009

39th AIAA Fluid Dynamics Conference

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The heat transfer rate was measured using global phosphor thermography and the resulting images and heat transfer rate distributions were used to infer the state of the boundary layer on the windside, leeside and side surfaces. Boundary layer trips were used to force the boundary layer turbulent, and a study was conducted to determine the effectiveness of the trips with various heights. The experimental data highlighted in this test report were used determine the allowable roughness height for both the windside and side surfaces of the vehicle as well as provide for future tunnel-to-tunnel comparisons.

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Section: Windside Heatingsupporting

confidence: 54%

Section: Leeside Heatingcontrasting

confidence: 43%

Aerothermodynamic Characteristics of Boundary Layer Transition and Trip Effectiveness of the HIFiRE Flight 5 Vehicle

Berger

Rufer

Kimmel

et al. 2009

39th AIAA Fluid Dynamics Conference

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“…This was observed in higher-Reynolds number cases tested at CUBRC. 34 If transition occurs at the extreme low-limit of Reynolds number (6x10 5 ) this would correspond to an altitude of 39.4 km (492.5 sec). A more plausible transition altitude would be that derived from PSE stability analysis, corresponding to a length Reynolds number of 3.7x10 6 .…”

Section: Figure 10 Centerline Transition Reynolds Numbers From Wind Tmentioning

confidence: 99%

HIFiRE-5 Flight Vehicle Design

Kimmel

Adamczak

Berger

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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The Hypersonic International Flight Research Experimentation (HIFiRE) program is a hypersonic flight test program executed by the Air Force Research Laboratories (AFRL)and Australian Defence Science and Technology Organization (DSTO). HIFiRE flight 5 is devoted to measuring transition on a three-dimensional body. This paper summarizes payload configuration, trajectory, vehicle stability limits and roughness tolerances. Results show that the proposed configuration is suitable for testing transition on a three-dimensional body. Transition is predicted to occur within the test window, and a design has been developed that will allow the vehicle to be manufactured within prescribed roughness tolerances. I. Nomenclature

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“…Generally the transition patterns are similar to those observed for the HIFiRE-5 configuration in the CUBRC LENS I wind tunnel, with the exception of leading-edge transition, as noted in the discussion of the side surface below. 44 It should be noted that the AEDC elliptic cone transition patterns show no welldefined crossflow side lobes. This may be due to the sharp nose, which might be expected to destabilize the centerline, or simply due to lack of resolution due to the placement of sensors.…”

Section: Windside Heatingmentioning

confidence: 97%

Ground Test and Computation of Boundary Layer Transition on the Hypersonic International Flight Research and Experimentation (HIFiRE)-5 Vehicle

Kimmel¹,

Adamczak²,

Gosse³

et al. 2011

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Using Government drawings, specifications, or other data included in this document for any purpose other than Government procurement does not in any way obligate the U.S. Government. The fact that the Government formulated or supplied the drawings, specifications, or other data does not license the holder or any other person or corporation; or convey any rights or permission to manufacture, use, or sell any patented invention that may relate to them. This report was cleared for public release by the USAF 88 th Air Base Wing (88 ABW) Public Affairs Office (PAO) and is available to the general public, including foreign nationals. Copies may be obtained from the Defense Technical Information Center (DTIC) (http://www.dtic.mil).

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Reviews of Studies of Boundary Layer Transition in Hypersonic Flows Over Axisymmetric and Elliptic Cones Conducted in the CUBRC Shock Tunnels

Cited by 31 publications

References 11 publications

Aerothermodynamic Characteristics of Boundary Layer Transition and Trip Effectiveness of the HIFiRE Flight 5 Vehicle

Aerothermodynamic Characteristics of Boundary Layer Transition and Trip Effectiveness of the HIFiRE Flight 5 Vehicle

HIFiRE-5 Flight Vehicle Design

Ground Test and Computation of Boundary Layer Transition on the Hypersonic International Flight Research and Experimentation (HIFiRE)-5 Vehicle

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