Effect of Gas Injection on Transition in Hypervelocity Boundary Layers

Jewell, Joseph S.; Leyva, Ivett A.; Parziale, Nick J.; Shepherd, Joseph E.

doi:10.1007/978-3-642-25688-2_111

Cited by 29 publications

(27 citation statements)

References 10 publications

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“…The present work both overlaps and extends the parameters of the past studies, especially for low pressure and enthalpy. The R 2 values for the correlation between the two parameters are respectively 0.52 and 0.65 for the present N 2 and Air data sets, and respectively 0.10 and 0.59 for the Adam [1] and Jewell et al [5] data sets.…”

Section: Tunnel Operationmentioning

confidence: 58%

See 1 more Smart Citation

Shock Tunnel Operation and Correlation of Boundary Layer Transition on a Cone in Hypervelocity Flow

Jewell¹,

Shepherd²,

Leyva³

2013

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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 this 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 Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY) May 2013 REPORT TYPE Technical Paper DATES COVERED (From -To)May 2013-July 2013 TITLE AND SUBTITLEShock tunnel operation and correlation of boundary layer transition on a cone in hypervelocity flow SPONSOR/MONITOR'S REPORTEdwards AFB CA 93524-7048 NUMBER(S) AFRL-RQ-ED-TP-2013-123 DISTRIBUTION / AVAILABILITY STATEMENTDistribution A: Approved for Public Release; Distribution Unlimited. PA#13304 SUPPLEMENTARY NOTESConference paper for the 29th International Shock Wave Symposium, Madison, WI , 14-19 July 2013. ABSTRACTThe Caltech T5 reflected shock tunnel is used to produce hypervelocity flow over a range of velocities and pressures by varying the test gas and operating parameters of reservoir enthalpy (hres) and reservoir pressure (Pres). One area of research in T5 is the measurement of boundary layer behavior and transition from laminar to turbulent flow on a smooth 5-degree halfangle cone [3,1,11]. To design experiments that involve the measurement or manipulation of instability and transition processes (for example, Jewell et al. [7]), it is important to choose tunnel conditions for which the expected transition location is at least approximately known. In the present paper, we discuss the selection of tunnel operating parameters, the correlation of those parameters with measurements of boundary layer transition, and some observations on the analysis of transition location in terms of local boundary layer properties.

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Section: Tunnel Operationmentioning

confidence: 58%

“…For the uncertainties that can be quantified, we have combined these to obtain the error bounds on measured properties that are shown in this paper. The tunnel parameters for the present studies in air and nitrogen [5].…”

Section: Tunnel Operationmentioning

confidence: 99%

Shock Tunnel Operation and Correlation of Boundary Layer Transition on a Cone in Hypervelocity Flow

Jewell¹,

Shepherd²,

Leyva³

2013

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“…Relying on an extensive database from past operation and calibration of the tunnel performance, the flow Reynolds number and location of transition to turbulence on the cone model can be adjusted so that repeatable observations can be made of the onset and growth of instabilities in an initially laminar boundary layer. The location of boundary-layer transition is identified by departure from laminar surface heat-flux rates measured by surface-mounted heat-transfer gauges, as discussed in Jewell et al (2011, 2012), Jewell, Shepherd & Leyva (2013a, Jewell et al (2013b) andJewell (2014). Operating conditions for T5 are selected on the basis of these heat-flux measurements and, more importantly, the FLDI measurements provided a clear indication of the nature of the flow at those measurement locations.…”

Section: Focused Laser Differential Interferometrymentioning

confidence: 99%

Observations of hypervelocity boundary-layer instability

2015

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A novel optical method is used to measure the high-frequency (up to 3 MHz) density fluctuations that precede transition to turbulence within a laminar boundary layer in a hypervelocity flow. This optical method, focused laser differential interferometry, enables measurements of short-wavelength, high-frequency disturbances that are impossible with conventional instrumentation such as pressure transducers or hot wires. In this work, the T5 reflected-shock tunnel is used to generate flows in air, nitrogen and carbon dioxide with speeds between 3.5 and 5 km s ), density fluctuations are observed to grow in amplitude and transition from a single narrow band of frequencies consistent with the Mack or second mode of boundary-layer instability to bursts of large-amplitude and spectrally broad disturbances that appear to be precursors of turbulent spots. Disturbances that are sufficiently small in initial amplitude have a wavepacket-like signature and are observed to grow in amplitude between the upstream and downstream measurement locations. A cross-correlation analysis indicates propagation of wavepackets at speeds close to the edge velocity. The free stream flow created by the shock tunnel and the resulting boundary layer on the cone are computed, accounting for chemical and vibrational non-equilibrium processes. Using this base flow, local linear and parabolized stability (PSE) analyses are carried out and compared with the experimental results. Reasonable agreement is found between measured and predicted most unstable frequencies, with the greatest differences being approximately 15 %. The scaling of the observed frequency with the inverse of boundary-layer thickness and directly with the flow velocity are consistent with the characteristics of Mack's second mode, as well as results of previous researchers on hypersonic boundary layers.

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“…This configuration is similar to that tested at Caltech's T5 shock tunnel [6,8]. B) Baseline configuration with shaping of the injection region; C) Baseline configuration with the normal-wall suction and blowing of zero net injection.…”

Section: Introductionmentioning

confidence: 98%

“…In Ref. [8], transition delays were documented in shots with CO 2 injection. The data showed a general trend of increasing delay with injection rate, before a sharp drop-off at the highest injection rate.…”

Section: Introductionmentioning

confidence: 99%

Theoretical-Numerical Analysis of Boundary-Layer Stability with Combined Injection and Acoustic Absorptive Coating

Федоров¹,

Soudakov²

2014

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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 the burden, to Department of Defense, Washington Headquarters Services, Directorate for Information Operations and Reports (0704-0188), 1215 Jefferson Davis Highway, Suite 1204, Arlington, VA 22202-4302. Respondents should be aware that notwithstanding any other provision of law, no person shall be subject to any penalty for failing to comply with a collection of information if it does not display a currently valid OMB control number. PLEASE DO NOT RETURN YOUR FORM TO THE ABOVE ADDRESS. REPORT DATE (DD-MM-YYYY)24 January 2014 REPORT TYPE Final Report PERFORMING ORGANIZATION NAME(S) AND ADDRESS(ES)Moscow Institute of Physics and Technology 9, Institutskii per. Dolgoprudny, Moscow Region, 141700 Russia PERFORMING ORGANIZATION REPORT NUMBERN/A SPONSORING/MONITORING AGENCY NAME(S) AND ADDRESS(ES)Oleksiy SPONSOR/MONITOR'S ACRONYM(S)AFRL/AFOSR/IOE (EOARD) SPONSOR/MONITOR'S REPORT NUMBER(S) AFRL-AFOSR-UK-TR-2014-000112. DISTRIBUTION/AVAILABILITY STATEMENT Distribution A: Approved for public release; distribution is unlimited. SUPPLEMENTARY NOTES ABSTRACTThis report summarizes results of stability analyses performed for a slender sharp cone with and without injection of air through a porous strip. The free-stream parameters are related to the experiments in the Caltech's T5 shock tunnel. The analysis is focused on pure aerodynamic effects in the framework of perfect gas model. It was shown that the injection leads to destabilization of acoustic modes in the near-field relaxation region. To reduce this detrimental effect it was suggested to alter the injector surface shape or use suction-blowing of zero net injection. However, stability computations showed that these modifications did not improve the injector performance. The porous wall effect on the acoustic instability was also examined. It was found that porosity stabilizes the boundary layer flow with and without injection. This indicates that the injector performance can be improved, if the porous layer, which is used for the injection, is protruded downstream to cover the near-filed relaxation region. SUBJECT TERMSEOARD, Boundary Layer, BL absorption, BL stability, BL injuection, hyperconic BL 1 AbstractThis report summarizes results of stability analyses performed for a slender sharp cone with and without injection of air through a porous strip. The free-stream parameters are related to the experiments in the Caltech's T5 shock tunnel. The analysis is focused on pure aerodynamic effects in the framework of perfect gas model. It was shown that the injection leads to destabilization of acoustic modes in the near-field relaxation region. To reduce ...

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Effect of Gas Injection on Transition in Hypervelocity Boundary Layers

Cited by 29 publications

References 10 publications

Shock Tunnel Operation and Correlation of Boundary Layer Transition on a Cone in Hypervelocity Flow

Shock Tunnel Operation and Correlation of Boundary Layer Transition on a Cone in Hypervelocity Flow

Observations of hypervelocity boundary-layer instability

Theoretical-Numerical Analysis of Boundary-Layer Stability with Combined Injection and Acoustic Absorptive Coating

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