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Full Length Article | Open Access

Investigation of influence of local cooling/heating on nonlinear instability of high-speed boundary layer with direct numerical simulations

Teng ZHOU,Yuhan LUChao YAN( )
School of Aeronautic Science and Engineering, Beihang University, Beijing 100191, China

Peer review under responsibility of Editorial Committee of CJA.

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Abstract

The influence of local cooling/heating on two types of nonlinear instabilities of the high-speed boundary layer, namely, the First and Second Mode Oblique Breakdown (FMOB and SMOB), is studied using direct numerical simulations. Local cooling and heating are performed at the weak and strong nonlinear stages of the two types of nonlinear instabilities. It is found that for the FMOB, local cooling at the weak nonlinear region will suppress the increase of the fundamental mode, leading to transition delay. Opposite to local cooling, local heating at the weak nonlinear region of the FMOB will promote the growth of the fundamental mode, resulting in the occurrence of more upstream transition onset. However, if local cooling and heating are performed at the strong nonlinear region, the influence of both local cooling and heating on the FMOB can be neglected. Remarkably, both local heating and cooling can delay the SMOB for different mechanisms. Performing local cooling at the weak nonlinear region of the SMOB, the low amplitude of higher spanwise wavenumber steady mode caused by local cooling lies behind transition delay. When local cooling is set at the strong nonlinear region, the low amplitude of harmonic modes around the cooling area can cause transition delay. Additionally, local heating will suppress the SMOB for the slowing amplification rate of various modes caused by the local heating at both the weak and strong nonlinear stages of the SMOB.

References

1

Zhu WK, Shi MT, Zhu YD, et al. Experimental study of hypersonic boundary layer transition on a permeable wall of a flared cone. Phys Fluids 2020;32(1):011701.

2

Zhu WK, Chen X, Zhu YD, et al. Nonlinear interactions in the hypersonic boundary layer on the permeable wall. Phys Fluids 2020;32(10):104110.

3

Zhu WK, Gu DW, Si WF, et al. Instability evolution in the hypersonic boundary layer over a wavy wall. J Fluid Mech 2022;943:A16.

4

Zhang TX, Chen JQ, Zhao YT, et al. A three-equation transition model with mechanical considerations. Chin J Aeronaut 2022;35(11):178–90.

5

Hartman AB, Hader C, Fasel HF. Nonlinear transition mechanism on a blunt cone at Mach 6: Oblique breakdown. J Fluid Mech 2021;915:R2.

6

Zhou T, Liu ZJ, Yan C. Linear and nonlinear instabilities of a high-speed boundary layer on porous coating. AIAA J 2022;61(1):489–96.

7

Zhao YT, Chen JQ, Zhao R, et al. Assessment and improvement of k-ω-γ model for separation-induced transition prediction. Chin J Aeronaut 2022;35(11):219–34.

8

Zhao R, Liu T, Wen CY, et al. Impedance-near-zero acoustic metasurface for hypersonic boundary-layer flow stabilization. Phys Rev Applied 2019;11(4):044015.

9

Zhou L, Zhao R, Yuan W. Application of improved k-ω-γ transition model to hypersonic complex configurations. AIAA J 2019;57(5):2214–21.

10

Inger GR, Gnoffo PA. Analytical and computational study of wall temperature jumps in supersonic flow. AIAA J 2001;39(1):79–87.

11
Mack L. Boundary-layer linear stability theory. Pasadena: California Inst of Tech Pasadena Jet Propulsion Lab, 1984. Report No.: 709, Part 3.
12

Paredes P, Choudhari MM, Li F. Instability wave–streak interactions in a supersonic boundary layer. J Fluid Mech 2017;831:524–53.

13
Thumm A, Wolz W, Fasel H. Numerical simulation of spatially growing three-dimensional disturbance waves in compressible boundary layers. Laminar-turbulent transition. Berlin: Springer; 1990. p. 303–8.
14
Fasel H, Thumm A, Bestek H. Direct numerical simulation of transition in supersonic boundary layers: Oblique breakdown. Fluids engineering conference. Washington, D.C: ASME; 1993. p. 77–92.
15
Fezer A, Kloker M. Spatial direct numerical simulation of transition phenomena in supersonic flat-plate boundary layers. Laminar-turbulent transition. Berlin: Springer; 2000. p. 415–20.
16

Mayer CSJ, Wernz S, Fasel HF. Numerical investigation of the nonlinear transition regime in a Mach 2 boundary layer. J Fluid Mech 2011;668:113–49.

17

Chang CL, Malik MR. Oblique-mode breakdown and secondary instability in supersonic boundary layers. J Fluid Mech 1994;273:323–60.

18

Mayer CSJ, Von Terzi DA, Fasel HF. Direct numerical simulation of complete transition to turbulence via oblique breakdown at Mach 3. J Fluid Mech 2011;674:5–42.

19

Kosinov AD, Maslov AA, Semionov NV. An experimental study of generation of unstable disturbances on the leading edge of a plate at M=2. J Appl Mech Tech Phys 1997;38(1):45–51.

20

Sivasubramanian J, Fasel HF. Direct numerical simulation of transition in a sharp cone boundary layer at Mach 6: Fundamental breakdown. J Fluid Mech 2015;768:175–218.

21

Chen X, Zhu YD, Lee CB. Interactions between second mode and low-frequency waves in a hypersonic boundary layer. J Fluid Mech 2017;820:693–735.

22

Zhang CB, Luo JS. Selective enhancement of oblique waves caused by finite amplitude second mode in supersonic boundary layer. Appl Math Mech -Engl Ed 2017;38(8):1109–26.

23
Husmeier F, Fasel H. Numerical investigations of hypersonic boundary layer transition over circular cones. Reston: AIAA; 2007. Report No: AIAA-2007-3843.
24

Pruett CD, Chang CL. Spatial direct numerical simulation of high-speed boundary-layer flows Part Ⅱ: transition on a cone in Mach 8 flow. Theoret Comput Fluid Dyn 1995;7(5):397–424.

25

Franko KJ, Lele SK. Breakdown mechanisms and heat transfer overshoot in hypersonic zero pressure gradient boundary layers. J Fluid Mech 2013;730:491–532.

26

Zhou T, Liu ZJ, Lu YH, et al. Direct numerical simulation of complete transition to turbulence via first- and second-mode oblique breakdown at a high-speed boundary layer. Phys Fluids 2022;34(7):074101.

27

Novikov A, Egorov I, Fedorov A. Direct numerical simulation of wave packets in hypersonic compression-corner flow. AIAA J 2016;54(7):2034–50.

28

Unnikrishnan S, Gaitonde DV. First-mode-induced nonlinear breakdown in a hypersonic boundary layer. Comput Fluids 2019;191:104249.

29

Li JP, Chen SS, Cai FJ, et al. Bayesian uncertainty analysis of SA turbulence model for supersonic jet interaction simulations. Chin J Aeronaut 2022;35(4):185–201.

30

Meng TT, Li X, Zhou L, et al. Large eddy simulation and combined control of corner separation in a compressor cascade. Phys Fluids 2022;34(7):075113.

31
Soudakov VG, Egorov IV, Fedorov AV. Numerical simulation of receptivity of a hypersonic boundary layer over a surface with temperature jump. 6th European symposium on aerothermodynamics for space vehicles. Paris: ESA; 2009. p. 659–66.
32
Oz F, Kara K. Effects of local cooling on hypersonic boundarylayer stability. Reston: AIAA; 2021. Report No: AIAA-2021-0940.
33

Fedorov A, Soudakov V, Egorov I, et al. High-speed boundary-layer stability on a cone with localized wall heating or cooling. AIAA J 2015;53(9):2512–24.

34

Zhao R, Wen CY, Tian XD, et al. Numerical simulation of local wall heating and cooling effect on the stability of a hypersonic boundary layer. Int J Heat Mass Transf 2018;121:986–98.

35

Celep M, Hadjadj A, Shadloo MS, et al. Effect of streak employing control of oblique-breakdown in a supersonic boundary layer with weak wall heating/cooling. Phys Rev Fluids 2022;7(5):053904.

36

Zhou T, Lu YH, Liu ZJ, et al. Direct numerical simulation of control of oblique breakdown in a supersonic boundary layer using a local cooling strip. Phys Fluids 2021;33(8):084101.

37

Zhou T, Liu ZJ, Lu YH, et al. Control of oblique breakdown in a supersonic boundary layer employing a local cooling strip. J Fluid Mech 2022;949:A4.

38

Li XL, Fu DX, Ma YW, et al. Development of high accuracy CFD software hoam-OpenCFD. E Sci Technol Appl 2010;1(1):53–9.

39

Li XL, Fu DX, Ma YW. Direct numerical simulation of hypersonic boundary layer transition over a blunt cone with a small angle of attack. Phys Fluids 2010;22(2):025105.

40

Li XL, Tong FL, Yu CP, et al. Statistical analysis of temperature distribution on vortex surfaces in hypersonic turbulent boundary layer. Phys Fluids 2019;31(10):106101.

41

Li XL, Leng Y, He ZW. Optimized sixth-order monotonicity-preserving scheme by nonlinear spectral analysis. Int J Numer Meth Fluids 2013;73(6):560–77.

42

Steger JL, Warming RF. Flux vector splitting of the inviscid gasdynamic equations with application to finite-difference methods. J Comput Phys 1981;40(2):263–93.

43

Jiang GS, Shu CW. Efficient implementation of weighted ENO schemes. J Comput Phys 1996;126(1):202–28.

44

Stewartson K. The theory of laminar boundary layers in compressible fluids. Oxford: Clarendon Press; 1964.

45

Sharma S, Shadloo MS, Hadjadj A, et al. Control of oblique-type breakdown in a supersonic boundary layer employing streaks. J Fluid Mech 2019;873:1072–89.

Chinese Journal of Aeronautics
Pages 77-87
Cite this article:
ZHOU T, LU Y, YAN C. Investigation of influence of local cooling/heating on nonlinear instability of high-speed boundary layer with direct numerical simulations. Chinese Journal of Aeronautics, 2023, 36(12): 77-87. https://doi.org/10.1016/j.cja.2023.07.017

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Received: 14 November 2022
Revised: 13 December 2022
Accepted: 03 January 2023
Published: 25 July 2023
© 2023 Chinese Society of Aeronautics and Astronautics.

This is an open access article under the CC BY-NC-ND license (http://creativecommons.org/licenses/by-nc-nd/4.0/).

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