Hostname: page-component-848d4c4894-m9kch Total loading time: 0 Render date: 2024-05-04T14:47:40.528Z Has data issue: false hasContentIssue false
  • English
  • Français

Dilatational-wave-induced aerodynamic cooling in transitional hypersonic boundary layers

Published online by Cambridge University Press:  29 January 2021

Yiding Zhu Open the ORCID record for Yiding Zhu [Opens in a new window] ,
Dingwei Gu ,
Wenkai Zhu Open the ORCID record for Wenkai Zhu [Opens in a new window] ,
Shiyi Chen ,
Cunbiao Lee Open the ORCID record for Cunbiao Lee [Opens in a new window]  and
Elaine S. Oran
Yiding Zhu
Affiliation:
State Key Laboratory of Turbulence and Complex Systems, Collaborative Innovation Center for Advanced Aero-Engines, Peking University, Beijing100871, PR China
Dingwei Gu
Affiliation:
State Key Laboratory of Turbulence and Complex Systems, Collaborative Innovation Center for Advanced Aero-Engines, Peking University, Beijing100871, PR China
Wenkai Zhu
Affiliation:
State Key Laboratory of Turbulence and Complex Systems, Collaborative Innovation Center for Advanced Aero-Engines, Peking University, Beijing100871, PR China
Shiyi Chen
Affiliation:
State Key Laboratory of Turbulence and Complex Systems, Collaborative Innovation Center for Advanced Aero-Engines, Peking University, Beijing100871, PR China
Cunbiao Lee*
Affiliation:
State Key Laboratory of Turbulence and Complex Systems, Collaborative Innovation Center for Advanced Aero-Engines, Peking University, Beijing100871, PR China
Elaine S. Oran
Affiliation:
Department of Aerospace Engineering, University of Maryland, College Park, MD20742, USA
*
†Email address for correspondence: cblee@mech.pku.edu.cn
Get access Rights & Permissions [Opens in a new window]

Abstract

The evolution of an instability in a transitional hypersonic boundary layer and its effects on aerodynamic cooling are investigated over 260-mm-long flared cone models with smooth and porous surfaces. Experiments are conducted in a Mach 6 wind tunnel using Rayleigh-scattering flow visualization, fast-response pressure sensors and an infrared camera. Calculations are performed based on both direct numerical simulations (DNS) and linear stability theory (LST). The unit Reynolds number is $9.7 \times 10^6\ \textrm {m}^{-1}$. It is confirmed that a cooled region appears downstream of the local heat peak as the second-mode instability evolves over the smooth-surface model, as found in other studies. Comparisons between the DNS and LST results show that the nonlinear interaction of the second mode causes the phase difference $\phi _{p\theta }$ to change between the periodic pressure and dilatation waves. This forms a negative cycle-averaged pressure dilatation near the wall and creates the cooled region. Further, by using porous steel to modify the sound admittance of the model surface, it is possible to artificially obtain negative cycle-averaged pressure dilatation near the wall, and thus reduce the surface heat flux by approximately 28 %. These results indicate the possibility of precisely controlling the pressure-dilatation-induced aerodynamic heating through the modification of surface sound admittance.

JFM classification

Compressible Flows: Compressible boundary layers Boundary Layers: Boundary layer stability Aerodynamics: High-speed flow
Type
JFM Papers
Information
Journal of Fluid Mechanics , Volume 911 , 25 March 2021 , A36
Check for updates
Copyright
© The Author(s), 2021. Published by Cambridge University Press

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

References

REFERENCES

Allard, J.-F. & Daigle, G. 2009 Propagation of Sound in Porous Media: Modelling Sound Absorbing Materials, 2nd edn. Wiley-Blackwell.CrossRefGoogle Scholar
Beckwith, I.E. & Moore, W.O. 1982 Mean flow and noise measurements in a Mach-3.5 pilot quiet tunnel. AIAA Paper 1982-0569.CrossRefGoogle Scholar
Berridge, D.C., Chou, A., Ward, C.A.C., Steen, L.E., Gilbert, P.L., Juliano, T.J., Schneider, S.P. & Gronvall, J.E. 2010 Hypersonic boundary-layer transition experiments in a Mach-6 quiet tunnel. AIAA Paper 2010-1061.CrossRefGoogle Scholar
Bountin, D.A., Shiplyuk, A.N. & Sidorenko, A.A. 2000 Experimental investigations of disturbance development in the hypersonic boundary layer on a conical model. In Laminar-Turbulent Transition (ed. H.F. Fasel & W.S. Saric), pp. 475–480. Springer.CrossRefGoogle Scholar
Casper, K.M., Beresh, S.J. & Schneider, S.P. 2014 Pressure fuctuations beneath instability wavepackets and turbulent spots in a hypersonic boundary layer. J. Fluid Mech. 756, 1058–1091.CrossRefGoogle Scholar
Chen, X., Zhu, Y.D. & Lee, C.B. 2017 Interactions between second mode and low-frequency waves in a hypersonic boundary layer. J. Fluids Mech. 820, 693–735.CrossRefGoogle Scholar
Chokani, N., Bountin, D.A., Shiplyuk, A.N. & Maslov, A.A. 2005 Nonlinear aspects of hypersonic boundary-layer stability on a porous surface. AIAA J. 43 (1), 149–155.CrossRefGoogle Scholar
Cook, W.J. & Felderman, E.J. 1965 Reduction of data from thin-film heat-transfer gages: a concise numerical technique. AIAA J. 4 (3), 561–562.CrossRefGoogle Scholar
Craig, S., Humble, R., Hofferth, J. & Saric, W. 2019 Nonlinear behaviour of the mack mode in a hypersonic boundary layer. J. Fluid Mech. 872, 74–99.CrossRefGoogle Scholar
Fedorov, A., Shiplyuk, A., Maslov, A., Burov, E. & Malmuth, N. 2003 Stabilization of a hypersonic boundary layer using an ultrasonically absorptive coatings. J. Fluid Mech. 479, 99–124.CrossRefGoogle Scholar
Fedorov, A.V. 2011 Transition and stability of high-speed boundary layers. Annu. Rev. Fluid Mech. 43, 79–95.CrossRefGoogle Scholar
Fedorov, A.V., Malmuth, N.D., Rasheed, A. & Hornung, H.G. 2001 Stabilization of hypersonic boundary layers by porous coatings. AIAA J. 39 (4), 605–610.CrossRefGoogle Scholar
Franko, K.J. & Lele, S.K. 2013 Breakdown mechanisms and heat transfer overshoot in hypersonic zero pressure gradient boundary layers. J. Fluid Mech. 730, 491–532.CrossRefGoogle Scholar
Fujii, K. 2006 Experiment of two dimensional roughness effect on hypersonic boundary-layer transition. J. Spacecr. Rockets 43 (4), 731–738.CrossRefGoogle Scholar
Kim, H.-K. & Lee, H.-K. 2010 Acoustic absorption modeling of porous concrete considering the gradation and shape of aggregates and void ratio. J. Sound Vib. 329 (7), 866–879.CrossRefGoogle Scholar
Kovasznay, L.S.G. 1953 Turbulence in supersonic flow. J. Aeronaut. Sci. 20, 657–674.CrossRefGoogle Scholar
Kuehl, J.J. 2018 Thermoacoustic interpretation of second mode instability. AIAA J. 56, 3585–3592.CrossRefGoogle Scholar
Laufer, J. 1961 Aerodynamic noise in supersonic wind tunnels. J. Aerosp. Sci. 28, 685–692.CrossRefGoogle Scholar
Lee, C.B. & Chen, S.Y. 2019 Recent progress in the study of transition in the hypersonic boundary layer. Natl Sci. Rev. 6, 155–170.CrossRefGoogle Scholar
Lee, C.B. & Jiang, X.Y. 2019 Flow structures in transitional and turbulent boundary layers. Phys. Fluids 31, 111301.Google Scholar
Li, X., Fu, D. & Ma, Y. 2010 Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack. Phys. Fluids 22, 025105.CrossRefGoogle Scholar
Mack, L.M. 1969 Boundary-layer stability theory. Jet Propulsion Laboratory Document No. 900-277.Google Scholar
Malik, M.R. & Spall, R.E. 1991 On the stability of compressible flow past axisymmetric bodies. J. Fluid Mech. 228, 443–463.Google Scholar
Malmuth, N., Fedorovf, A., Shalaevt, V., Cole, J., Khokhlov, A., Hites, M. & Williams, D. 1998 Problems in high speed flow prediction relevant to control. AIAA Paper 1998-2695.CrossRefGoogle Scholar
Maslov, A.A., Mironov, S.G., Poplavskaya, T.V. & Kirilovskiy, S.V. 2005 Supersonic flow around a cylinder with a permeable high-porosity insert: experiment and numerical simulation. AIAA J. 43 (1), 149–155.Google Scholar
Mittal, A. & Girimaji, S.S. 2020 Nonlinear evolution of perturbations in high mach number wall-bounded flow: pressure–dilatation effects. Phys. Fluids 32, 036101.CrossRefGoogle Scholar
Pruett, C.D. & Chang, C.-L. 1998 Direct numerical simulation of hypersonic boundary-layer flow on a flared cone. Theor. Comput. Fluid Dyn. 11, 40–67.CrossRefGoogle Scholar
Rasheed, A., Hornung, H.G., Fedorov, A.V. & Malmuth, N.D. 2001 Experiments on passive hypervelocity boundary layer control using a porous surface. AIAA Paper 2001-0274.CrossRefGoogle Scholar
Schneider, S.P. 2013 Developing mechanism-based methods for estimating hypersonic boundary-layer transition in flight: the role of quiet tunnels. AIAA Paper 2013-2608.CrossRefGoogle Scholar
Shiplyuk, A.N., Bountin, D.A., Maslov, A.A. & Chokani, N. 2003 Nonlinear interactions of second mode instability with natural and artficial disturbances. AIAA Paper 2003-787.CrossRefGoogle Scholar
Si, W.F., Huang, G.L., Zhu, Y.D., Chen, S.Y. & Lee, C.B. 2019 Hypersonic aerodynamic heating over a flared cone with wavy wall. Phys. Fluids 31, 051702.Google Scholar
Sivasubramanian, J. & Fasel, H.F. 2014 Numerical investigation of the development of threedimensional wavepackets in a sharp cone boundary layer at Mach 6. J. Fluid Mech. 756, 600–649.CrossRefGoogle Scholar
Sivasubramanian, J. & Fasel, H.F. 2015 Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: fundamental breakdown. J. Fluid Mech. 768, 175–218.CrossRefGoogle Scholar
Smits, A.J. & Lim, T.T. 2000 Flow Visualization: Techniques and Examples. Imperial College Press.CrossRefGoogle Scholar
Stainback, P.C. 1972 A comparison of disturbance levels measured in hypersonic tunnels using a hot-wire anemometer and a pitot pressure probe. AIAA Paper 72–1003.CrossRefGoogle Scholar
Stetson, K.F. & Kimmel, R.L. 1992 On hypersonic boundary-layer stability. AIAA Paper 1992-0737.CrossRefGoogle Scholar
Stetson, K.F., Thompson, E.R., Donaldson, J.C. & Siler, L.G. 1983 Laminar boundary layer stability experiments on a cone at Mach 8, Part 1: sharp cone. AIAA Paper 1983-1761.Google Scholar
Stetson, K.F., Thompson, E.R., Donaldson, J.C. & Siler, L.G. 1984 Laminar boundary layer stability experiments on a cone at Mach 8, Part 2: blunt cone. AIAA Paper 84-0006.Google Scholar
Stetson, K.F., Thompson, E.R., Donaldson, J.C. & Siler, L.G. 1985 Laminar boundary layer stability experiments on a cone at Mach 8, Part 3: sharp cone at angle of attack. AIAA Paper 85-0492.Google Scholar
Stinson, M.R. & Champoux, Y. 1992 Propagation of sound and the assignment of shape factors in model porous materials having simple pore geometries. J. Acoust. Soc. Am. 91 (2), 685–695.Google Scholar
Stinson, M.R. & Shaw, E.A.G. 1985 Acoustic impedance of small, circular orifices in thin plates. J. Acoust. Soc. Am. 77 (6), 2039–2042.CrossRefGoogle Scholar
Sun, B.H. & Oran, E.S. 2018 New principle for aerodynamic heating. Natl Sci. Rev. 5 (5), 606–607.CrossRefGoogle Scholar
Wang, X. & Zhong, X. 2011 Phase angle of porous coating admittance and its effect on boundary-layer stabilization. AIAA Paper 2011-3080.CrossRefGoogle Scholar
Zhang, C.H., Tang, Q. & Lee, C.B. 2013 Hypersonic boundary-layer transition on a flared cone. Acta Mechanica Sin. 29 (1), 48–53.CrossRefGoogle Scholar
Zhang, C.H., Zhu, Y.D., Chen, X., Yuan, H.J., Wu, J.Z., Chen, S.Y., Lee, C.B. & Gad-el-hak, M. 2015 Transition in hypersonic boundary layers. AIP Adv. 5, 107137.CrossRefGoogle Scholar
Zhong, X.L. & Wang, X.W. 2012 Direct numerical simulation on the receptivity, instability, and transition of hypersonic boundary layers. Annu. Rev. Fluid Mech. 44, 527–561.CrossRefGoogle Scholar
Zhu, W.K., Shi, M.T., Zhu, Y.D. & Lee, C.B. 2019 a Experimental study of hypersonic boundary layer transition on a permeable wall of a flared cone. Phys. Fluids 32, 011701.Google Scholar
Zhu, W.K., Shi, M.T., Zhu, Y.D. & Lee, C.B. 2019 b Experimental study of hypersonic boundary layer transition on a permeable wall of a flared cone. Phys. Fluids 32, 011701.Google Scholar
Zhu, Y.D., Chen, X., Wu, J.Z., Chen, S.Y., Lee, C.B. & Gad-el-Hak, M. 2018 a Aerodynamic heating in transitional hypersonic boundary layers: role of second mode instability. Phys. Fluids 30, 011701.CrossRefGoogle Scholar
Zhu, Y.D., Lee, C.B., Chen, X., Wu, J.Z., Chen, S.Y. & Gad-el-Hak, M. 2018 b Newly identified principle for aerodynamic heating in hypersonic flows. J. Fluid Mech. 855, 152–180.CrossRefGoogle Scholar
Zhu, Y.D., Zhang, C.H., Chen, X., Yuan, H.J., Wu, J.Z., Chen, S.Y., Lee, C.B. & Gad-el-Hak, M. 2016 Transition in hypersonic boundary layers: role of dilatational waves. AIAA J. 54 (10), 3039–3049.CrossRefGoogle Scholar

Zhu et al. supplementary movie 1

Time variation in Temperature and Temperature growth ratio after the hypersonic wind tunnel starts, arising from IR camera measurement.

Download Zhu et al. supplementary movie 1(Video)
Video 1.7 MB

Zhu et al. supplementary movie 2

Top two) Evolution of pressure and dilatation waves in hypersonic wall-bounded flows. (Bottom) Time variation in Wpθ and its time-averaged value respectively for heating region and cooling region.

Download Zhu et al. supplementary movie 2(Video)
Video 6.3 MB
Supplementary material: PDF

Zhu et al. supplementary material

Supplementary fig and captions

Download Zhu et al. supplementary material(PDF)
PDF 197.4 KB