Measurements of boundary layer transition on cones at angle of attack for Mach numbers from 11 to 13

Holden, Michael; Bower, Daniel; Chadwick, Kenneth

doi:10.2514/6.1995-2294

Cited by 25 publications

(9 citation statements)

References 14 publications

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“…axial station. This result is similar to that obtained by Holden at Mach 11 on slender blunt cones at the angle of attack [13]. Here, the bluntness effects cause the entropy layer to be swallowed more rapidly on the windward side, increasing the momentum thickness and impeding the crossflow momentum transfer and further destabilizing the wind side.…”

Section: Selection Of Freestream Conditions and Facility Flow Calsupporting

confidence: 87%

Ground Test Studies of the HIFiRE-1 Transition Experiment Part 1: Experimental Results

Wadhams

Mundy

MacLean

et al. 2008

Journal of Spacecraft and Rockets

118

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As part of a two-phase experimental study to obtain detailed heating and pressure data over the full-scale hypersonic international flight research and experimentation (HIFiRE-1, formally FRESH FX-1) flight geometry, Calspan-University at Buffalo Research Center has completed a matrix of ground tests to determine the optimal flight geometry and instrumentation configuration necessary to make measurements of desired flow phenomena during the flight experiment. The primary objective of the HIFiRE-1 flight experiment is to collect high-quality flight data from integrated flight instrumentation to be used for computational fluid dynamic code and ground test facility validation in regions of boundary-layer transition, turbulent separated flow, and shock/boundary-layer interaction. To support this flight experiment, data have been obtained in the large energy national shock hypervelocity wind tunnel employing a full-scale model over a range of Mach numbers from 6.5 to 7.4 and Reynolds numbers from 0:5E 06 to 5:5E 6 duplicating the reentry trajectory. These points gave researchers the best chance to measure the transition process on the forecone and have a turbulent separated flow on the cylinder that reattached onto the flare section. These test condition ranges were determined directly from the nominal descent trajectory of the Australian-launched Terrier-Orion launch vehicle that will serve as the booster for HIFiRE-1. The entire experimental database will be compared to future flight data and used by computationalists to validate codes in regions of attached and separated laminar and turbulent flows with shock/boundary layer interaction. In addition to the experimental data, Calspan-University at Buffalo Research Center performed a large amount of computational fluid dynamic analyses to confirm and validate not only the tunnel flow conditions, but also the two-and threedimensional flows over the model itself. These detailed computational results will be presented in a Part 2 companion paper.

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Section: Selection Of Freestream Conditions and Facility Flow Calsupporting

confidence: 87%

Ground Test Studies of the HIFiRE-1 Transition Experiment Part 1: Experimental Results

Wadhams

Mundy

MacLean

et al. 2008

Journal of Spacecraft and Rockets

118

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show abstract

“…When compressibility and cooling effects are included, a relationship is found between a new crossflow Reynolds number and the maximum crossflow velocity at transition. This result has been verified with the yawedcone data of King (1991), Stetson (1982), and Holden et al (1994). The new crossflow Reynolds number is calculated solely from the basic-state profiles and, as such, it can aid in conceptual (only) transition prediction and design for 3-D boundary layers.…”

Section: Empirical Correlationssupporting

confidence: 57%

Control of Aerodynamic Flows. Delivery Order 0051: Transition Prediction Method Review Summary for the Rapid Assessment Tool for Transition Prediction (RATTraP)

Davis¹,

Reed²,

Youngren³

et al. 2005

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“…However, there exit some inconsistency to this problem, for instance, experiments of Muri [5] on a cone at a Mach number of 6 showed that for cones with large bluntness, transition becomes windside forward and leeside aft. Hollen's [6] experiment showed transition on both windside and leeside forward for large bluntness. Since experimental conditions such as wind tunnel disturbance and noise are difficult to control, whether the above conclusions are universal is unclear.…”

Section: Introductionmentioning

confidence: 96%

Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle of attack

苏彩虹

Heng

2007

Appl Math Mech

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Stability and transition prediction of hypersonic boundary layer on a blunt cone with small nose bluntness at zero angle of attack was investigated. The nose radius of the cone is 0.5 mm; the cone half-angle is 5 • , and the Mach number of the oncoming flow is 6. The base flow of the blunt cone was obtained by direct numerical simulation. The linear stability theory was applied for the analysis of the first mode and the second mode unstable waves under both isothermal and adiabatic wall condition, and e N method was used for the prediction of transition location. The N factor was tentatively taken as 10, as no experimentally confirmed value was available. It is found that the wall temperature condition has a great effect on the transition location. For adiabatic wall, transition would take place more rearward than those for isothermal wall. And despite that for high Mach number flows, the maximum amplification rate of the second mode wave is far bigger than the maximum amplification rate of the first mode wave, the transition location of the boundary layer with adiabatic wall is controlled by the growth of first mode unstable waves. The methods employed in this paper are expected to be also applicable to the transition prediction for the three dimensional boundary layers on cones with angle of attack.

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Measurements of boundary layer transition on cones at angle of attack for Mach numbers from 11 to 13

Cited by 25 publications

References 14 publications

Ground Test Studies of the HIFiRE-1 Transition Experiment Part 1: Experimental Results

Ground Test Studies of the HIFiRE-1 Transition Experiment Part 1: Experimental Results

Control of Aerodynamic Flows. Delivery Order 0051: Transition Prediction Method Review Summary for the Rapid Assessment Tool for Transition Prediction (RATTraP)

Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle of attack

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