Receptivity of the Mach-4 boundary layer on an elliptic cone to laser-generated localized freestream perturbations

Schmisseur, John D.; Schneider, Steven P.; Collicott, Steven H.

doi:10.2514/6.1998-532

Cited by 61 publications

(42 citation statements)

References 19 publications

Supporting

Mentioning

Contrasting

Order By: Relevance

“…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.…”

Section: Hifire-5 Experimentsmentioning

confidence: 99%

Transition Analysis for the HIFiRE-5 Vehicle

Choudhari

Chang

Jentink

et al. 2009

39th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

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...

show abstract

Section: Hifire-5 Experimentsmentioning

confidence: 99%

Transition Analysis for the HIFiRE-5 Vehicle

Choudhari

Chang

Jentink

et al. 2009

39th AIAA Fluid Dynamics Conference

View full text Add to dashboard Cite

show abstract

“…56,57,58,59,60,61,62,63 This prior work 56,57,58 demonstrated that the 2:1 elliptic cone would generate significant crossflow instability at hypersonic flight conditions and potentially exhibit leading-edge transition. Figure 63 illustrates the elliptic cone geometry and coordinate system.…”

Section: Vehicle Descriptionmentioning

confidence: 96%

HIFiRE-1 and HIFiRE-5 Test Results

Kimmel¹,

Adamczak²,

Borg³

et al. 2014

View full text Add to dashboard Cite

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.

show abstract

“…Salyer characterized the perturbation profile across the shock and compared it with the LDI results. The laser system used to generate the laser perturbation in the work done by Salyer [15][16][17][18], Schmisseur [21], and Ladoon [22,23] could not be readily resurrected for this project, so it could not be used to test the performance of the LDI.…”

Section: Motivation and Backgroundmentioning

confidence: 99%

Oscillations in a Forward-Facing Cavity Measured Using Laser-Differential Interferometry in a Hypersonic Quiet Tunnel

Segura¹

2007

View full text Add to dashboard Cite

AFOSR/NAUnclassified and Approved for Public Release M.S. thesis by Rodrigo Segura with development of LDI for Mach-6 quiet tunnel and measurements in Mach-4 quiet tunnel Laminar-turbulent transition is a pivotal factor for the design of hypersonic vehicles but the mechanisms that induce transition are not well understood. A laser differential interferometer (LDI) is a non-intrusive optical device that measures the optical path length difference between two laser beams. The LDI is a reliable calibrated instrument to assist the study of boundary layer instability-wave growth in hypersonic flow and has high sensitivity and frequency response. An LDI with a commercial balanced photodetector capable of detecting optical path length differences of lambda/21,000 from DC to 80 MHz was assembled and tested in the Purdue Quiet-Flow Ludwieg tube. Fluctuations in the subsonic region of a forward-facing cavity were measured with the LDI and compared to those detected with a Kulite pressure transducer at the base of the cavity. Predictions of self-resonating deep cavities were confirmed. The LDI was then adapted and transferred to the Boeing/AFOSR Mach-6 Quiet Tunnel. to give special thanks to Joan Jackson; she made me laugh and was patient and helpful even when I demanded her help on rather short notice. Joe Kline's technical assistance is appreciated.A great deal of contribution came from my fellow researchers.

show abstract

Receptivity of the Mach-4 boundary layer on an elliptic cone to laser-generated localized freestream perturbations

Cited by 61 publications

References 19 publications

Transition Analysis for the HIFiRE-5 Vehicle

Transition Analysis for the HIFiRE-5 Vehicle

HIFiRE-1 and HIFiRE-5 Test Results

Oscillations in a Forward-Facing Cavity Measured Using Laser-Differential Interferometry in a Hypersonic Quiet Tunnel

Contact Info

Product

Resources

About