Studies of laminar, transitional, and turbulent hypersonic flows over curved compression surfaces

Holden, Michael; Chadwick, Kenneth

doi:10.2514/6.1995-93

Cited by 21 publications

(15 citation statements)

References 2 publications

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“…The elliptic cone configuration was chosen as the test-article geometry based on extensive previous testing and analysis on elliptic cones. 18,19,20,21,22,23,24,25 This prior work 18,19,20 demonstrated that the 2:1 elliptic cone would generate significant crossflow instability at the flight conditions and potentially exhibit leading-edge transition. The 2:1 elliptic cone configuration also possesses ample internal volume for sensors and instrumentation.…”

Section: A Vehicle Descriptionmentioning

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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Section: A Vehicle Descriptionmentioning

confidence: 99%

HIFiRE-5 Flight Vehicle Design

Kimmel

Adamczak

Berger

et al. 2010

40th Fluid Dynamics Conference and Exhibit

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“…During the mid-1990s, several researchers investigated transition phenomena on elliptic cones. [3][4][5][6][7][8][9][10] The elliptic cone embodies much of the transition phenomena seen on hypersonic glide vehicles. These phenomena include traveling first and second-mode waves, stationary and traveling cross-flow waves 11 and leading edge attachment line flows.…”

Section: Introductionmentioning

confidence: 99%

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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“…As a point The elliptic cone configuration was chosen based on past ground test and CFD. During the mid-1990s, several researchers investigated hypersonic transition phenomena on elliptic cones [21][22][23][24][25][26][27][28]. Investigators examined 4:1 and 2:1 elliptic cones.…”

mentioning

confidence: 99%

Transition Analysis for the HIFiRE-5 Vehicle

Choudhari

Chang

Jentink

et al. 2009

39th AIAA Fluid Dynamics Conference

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The Hypersonic International Flight Research and Experimentation (HIFiRE) 5 flight experiment by Air Force Research Laboratories and Australian Defense Science and Technology Organization is designed to provide in-flight boundary-layer transition data for a canonical 3D configuration at hypersonic Mach numbers. This paper outlines the progress, to date, on boundary layer stability analysis for the HIFiRE-5 flight configuration, as well as for selected test conditions from the wind tunnel experiments supporting the flight test. At flow conditions corresponding to the end of the test window, rather large values of linear amplification factor are predicted for both second mode (N>40) and crossflow (N>20) instabilities, strongly supporting the feasibility of first in-flight measurements of natural transition on a fully three-dimensional hypersonic configuration. Additional results highlight the rich mixture of instability mechanisms relevant to a large segment of the flight trajectory, as well as the effects of angle of attack and yaw angle on the predicted transition fronts for ground facility experiments at Mach 6. Backgroundue to its influence on surface heat transfer, skin-friction drag, and flow-separation characteristics, prediction of boundary layer transition constitutes an important aspect of hypersonic vehicle design. Laminar to turbulent transition over realistic vehicle surfaces is often caused by surface roughness of sufficiently large magnitude. However, when the surface is relatively smooth, the transition process is initiated by linear instabilities of the laminar boundary layer. Typically, the second (or Mack) mode instability dominates transition in 2D and axisymmetric boundary layers with hypersonic edge Mach numbers, although centrifugal (i.e., Gortler) instabilities may also come into play when the surface has concave curvature along the streamwise direction. Three-dimensional boundary layers involve the additional mechanisms of stationary and traveling modes of crossflow instability and, depending on the geometric configuration, may include the attachment line instability as well [1].Regardless of the speed regime, linear stability correlations have been quite successful in predicting the onset of transition when a single instability mechanism dominates the transition process [2]. Mixed mode transition has been more challenging to predict because of possible nonlinear interactions between the relevant modes of instability. To account for the effect of such interactions, an ad hoc composite metric based on the linear amplification factors for the different instability mechanisms has sometimes been used for transition correlation (see, for instance, [3]). Recent work on crossflow instability in low-speed boundary layers [4] has exposed additional shortcomings in applying purely linear predictive models to crossflow dominated transition in 3D boundary layers.The simplest canonical configuration that includes the necessary elements for studying both mixed mode transition and crossflow evolu...

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Studies of laminar, transitional, and turbulent hypersonic flows over curved compression surfaces

Cited by 21 publications

References 2 publications

HIFiRE-5 Flight Vehicle Design

HIFiRE-5 Flight Vehicle Design

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

Transition Analysis for the HIFiRE-5 Vehicle

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