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

Berger, Karen T.; Rufer, Shann J.; Kimmel, Roger L.; Adamczak, David

doi:10.2514/6.2009-4055

Cited by 39 publications

(20 citation statements)

References 25 publications

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“…During descent, latest (highest Reynolds number) leading edge transition occurred when the diameter Reynolds number at the most upstream joint was 1. The minor axis (centerline) transitioned at a lower Reynolds number than the leading edge, which is consistent with prior CFD 69,70 and wind tunnel measurements 53,65 at hypersonic conditions that indicated that the centerline is more unstable and prone to lower Reynolds number transition. Centerline transition also showed a more gradual progression over time than the leading edge transition.…”

Section: Transition Resultssupporting

confidence: 77%

“…Prior tests in the NASA Langley 20-inch Mach 6 wind tunnel demonstrated that roughness-induced transition from these fasteners would not propagate to the instrumented side of the payload. 65 The primary aerothermal instrumentation for HIFiRE-5 consisted of Medtherm Corporation coaxial thermocouples. Type T (copper-constantan) thermocouples were installed in aluminum portions of the aeroshell and Type E (chromel-constantan) were installed in the steel portions.…”

Section: Vehicle Descriptionmentioning

confidence: 99%

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HIFiRE-1 and HIFiRE-5 Test Results

Kimmel¹,

Adamczak²,

Borg³

et al. 2014

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The public reporting burden for this collection of information is estimated to average 1 hour per response, including the time for reviewing instructions, searching existing data sources, gathering and maintaining the data needed, and completing and reviewing the collection of information. Send comments regarding this burden estimate or any other aspect of this collection of information, including suggestions for reducing this burden, to Department of Defense, Washington Headquarters Services, Directorate for Information AFRL/RQHF SPONSORING/MONITORING AGENCY REPORT NUMBER(S) AFRL-RQ-WP-TR-2014-0038 DISTRIBUTION/AVAILABILITY STATEMENTApproved for public release; distribution unlimited SUPPLEMENTARY NOTESPA Case Number: 88ABW-2014-3421; Clearance Date: 17 Jul 2014. ABSTRACTThe primary experiment for HIFiRE-1 was to measure boundary-layer transition in hypersonic flight on a 7 degree halfangle, axisymmetric cone with a 2.5 mm radius bluntness. A secondary experiment measured mean and fluctuating pressure, and heat transfer on a cylinder-33-degreee-flare geometry. The ascent provided smooth-body, low angle-ofattack, boundary-layer transition at Mach numbers greater than 5. The end of turbulent-to-laminar transition occurred at Reynolds numbers between 10.3 to 12.2 million. Second-mode N-factors of approximately 14 correlated transition. A diamond-shaped trip retained turbulent flow until reaching a roughness Reynolds number Rekk = 2200. During re-entry, transition was measured around the circumference of the cone at Reynolds numbers ranging from 3 million on the leeside to 5 million on the windward side. In the shock-boundary layer interaction, maximum sound pressure levels of 173 dB were recorded upstream of the flare, and 185 dB on the flare itself. The principal goal of HIFiRE-5 was to measure hypersonic boundary layer transition on an elliptic cone. The second stage booster failed to ignite, so the experiment reached a maximum Mach number of only 3. Nevertheless, supersonic pressure and temperature data were obtained under laminar and turbulent flow, and flight systems were validated. Traveling and stationary crossflow instabilities were clearly measured for HIFiRE-5 in ground test in a quiet flow tunnel. The frequency, phase speed, and wave angle were all in good agreement with computations.

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Section: Transition Resultssupporting

confidence: 77%

Section: Vehicle Descriptionmentioning

confidence: 99%

HIFiRE-1 and HIFiRE-5 Test Results

Kimmel¹,

Adamczak²,

Borg³

et al. 2014

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“…Roughness was applied using 2D (tape strips) and 3D (tape squares) to the HIFiRE-5 model leading edge in the NASA LaRC 20-inch Mach 6 wind tunnel. 33 Heat transfer measurements from these experiments were used to determine the transition location due to the roughness elements. The procedure to determine the transition location was similar to that outlined previously for smooth-body transition.…”

Section: A Discrete Roughness Correlations For the Frustummentioning

confidence: 99%

“…Figure 10 shows centerline transition Reynolds numbers derived from NASA LaRC Mach 6 wind tunnel heat transfer data. 33 The transition Reynolds numbers were extracted by plotting measured heat transfer rates in log-log coordinates. A straight line was fit to the sensibly laminar portion of the data, and another to the transitional portion of the data.…”

Section: Figure 7 Hifire-5 Reynolds Number and Mach Profilementioning

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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“…The follow-on effort under this ongoing analysis is focused on more thorough application of higher fidelity analysis tools and a deeper investigation of instability physics using numerical computations pertaining to both natural transition (see, for instance, Fig. 6.1) and the effect of boundary layer trips [44]. …”

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

Cited by 39 publications

References 25 publications

HIFiRE-1 and HIFiRE-5 Test Results

HIFiRE-1 and HIFiRE-5 Test Results

HIFiRE-5 Flight Vehicle Design

Transition Analysis for the HIFiRE-5 Vehicle

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