Linear stability analysis of hypersonic boundary layer on a flat-plate with thermal-chemical non-equilibrium effects

CHEN Xianliang; FU Song

doi:10.7638/kqdlxxb-2019.0155

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Linear stability analysis of hypersonic boundary layer on a flat-plate with thermal-chemical non-equilibrium effects

更新时间：2026-05-28

- Linear stability analysis of hypersonic boundary layer on a flat-plate with thermal-chemical non-equilibrium effects
- Vol. 38, Issue 2, Pages: 316-325(2020)
- 作者机构：
  
  清华大学航天航空学院,北京,100084
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2019.0155
  CLC： O357.4
- Published：2020
- 稿件说明：
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陈贤亮, 符松. 热化学非平衡高超声速平板边界层线性稳定性分析[J]. 空气动力学学报, 2020, 38(2): 316-325.

CHEN Xianliang, FU Song. Linear stability analysis of hypersonic boundary layer on a flat-plate with thermal-chemical non-equilibrium effects[J]. 2020, 38(2): 316-325.
陈贤亮, 符松. 热化学非平衡高超声速平板边界层线性稳定性分析[J]. 空气动力学学报, 2020, 38(2): 316-325. DOI： 10.7638/kqdlxxb-2019.0155.

CHEN Xianliang, FU Song. Linear stability analysis of hypersonic boundary layer on a flat-plate with thermal-chemical non-equilibrium effects[J]. 2020, 38(2): 316-325. DOI： 10.7638/kqdlxxb-2019.0155.

摘要

高超声速边界层流动转捩是近期空气动力学研究的热点问题。对于环境扰动较小的自然转捩过程，稳定性分析已被证明是研究扰动演化的重要手段。另一方面，高超声速边界层内的温度会随着马赫数的升高而快速上升，极高的温度会引起所谓的高温真实气体效应，使得量热完全气体假设失效，从而对边界层稳定性和转捩产生影响。本文针对高温热化学非平衡气体，利用空气5组分模型开展了平板边界层的线性稳定性分析，重点研究了热化学过程对模态稳定性的影响，并探究了边界层离散谱模态的演化和同步过程。研究表明，对于由第二模态主导的高超声速二维边界层：（1）扰动相比基本流更趋向于热化学冻结态；（2）扰动方程中新出现的非平衡源项的扰动项对稳定性影响很小，非平衡过程主要是通过改变基本流剖面来间接影响稳定性；（3）声速是影响第二及更高模态的重要参数，热化学平衡态假设引起的声速计算式的变化能够解释边界层温度和厚度降低时第二模态频率反而降低的非常规趋势。

Abstract

The research on hypersonic boundary layer transition is a recent focal point in aerodynamics. For the so-called 'natural transition'

where the level of environment disturbance is low

stability analysis has been proved to be a helpful technique in studying evolution of disturbances. On the other hand

temperatures in hypersonic boundary layer increase dramatically with Mach number. Extremely high-temperature causes the so-called 'real-gas effects'

or more exactly

'thermal-chemical non-equilibrium effects'

which invalidates the calorically perfect gas assumption

and inevitably influences the stability and transition process. The flow treated in this paper is a hypersonic boundary layer on a flat-plate with thermal-chemical non-equilibrium effects. Linear stability theory (LST) is applied to study the effects thermal-chemical process take on modal instability. Meanwhile

the evolution and synchronization process between discrete and continuous spectrum are explored. Results for the 2-D hypersonic boundary layer where the 2nd mode dominates are concluded as follows. Firstly

disturbances are more thermal-chemical frozen than the basic flow. Secondly

the new term in the disturbance equation introduced by the non-equilibrium source term has little effects on stability. The differences in stability behaviors between non-equilibrium and calorically perfect gas mainly attribute to different basic flow profiles. Thirdly

speed of sound is crucial to Mack modes. The different evaluation of the speed of sound for thermal-chemical equilibrium flow is the answer to the unconventional trend that a cooler and thinner boundary layer has lower 2nd-mode frequency.

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references

MORKOVIN M V, RESHOTKO E, HERBERT T. Transition in open flow systems-a reassessment[J]. Bulletin of the APS, 1994, 39(9):1-31.

CHEN J Q, TU G H, ZHANG Y F, et al. Hypersnonic boundary layer transition:what we know, where shall we go[J]. Acta Aerodynamica Sinica, 2017, 35(3):311-337. (in Chinese)

YANG W B, SHEN Q, ZHU D H, et al. Tendency and current status of hypersonic boundary layer transition[J]. Acta Aerodynamica Sinica, 2018, 36(2):183-195. (in Chinese)

ANDERSON J D. Hypersonic and high-temperature gas dynamics, second edition[M]. Reston, VA:AIAA, 2006.

TANNEHILL J C, MUGGE P H. Improved curve fits for the thermodynamic properties of equilibrium air suitable for numerical computation using time-dependent or shock capturing methods[R]. Iowa State University, 1974.

SRINIVASAN S, TANNEHILL J C, WEILMUENSTER K J. Simplified curve fits for the transport properties of equilibrium air: NASA CR-180422[R]. NASA contractor report, 1986.

GNOFFO P A, GUPTA R N, SHINN J. Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium: NASA-TP-2867[R]. Hampton, VANTRS: NASA Langley Research Center, 1989.

MALIK M R, ANDERSON E C. Real gas effects on hypersonic boundary-layer stability[J]. Physics of Fluids A:Fluid Dynamics, 1991, 3(5):803-821.

STUCKERT G, REED H L. Linear disturbances in hypersonic, chemically reacting shock layers[J]. AIAA Journal, 1994, 32(7):1384-1393.

FAN Y, WAN B B, HAN Y F, et al. Hydrodynamic stability and transition prediction with the chemical equilibrium gas model[J]. Journal of Aerospace Power, 2016, 31(7):1658-1668. (in Chinese)

WAN B B, HAN Y F, FAN Y, et al. Effect of transport properties of high-temperature air on boundary layer stability and transition prediction[J]. Journal of Aerospace Power, 2017, 32(1):188-195. (in Chinese)

HUDSON M L, CHOKANI N, CANDLER G V. Linear stability of hypersonic flow in thermochemical nonequilibrium[J]. AIAA Journal, 1997, 35:958-964.

JOHNSON H, SEIPP T, CANDLER G, et al. Numerical study of hypersonic reacting boundary layer transition on cones[C]//32nd Thermophysics Conference, Atlanta, GA, USA. Reston, Virigina: AIAA, 1997.

BERTOLOTTI F P. The influence of rotational and vibrational energy relaxation on boundary-layer stability[J]. Journal of Fluid Mechanics, 1998, 372:93-118.

MALIK M R. Hypersonic flight transition data analysis using parabolized stability equations with chemistry effects[J]. Journal of Spacecraft and Rockets, 2003, 40(3):332-344.

FEDOROV A, TUMIN A. High-speed boundary-layer instability:old terminology and a new framework[J]. AIAA Journal, 2011, 49(8):1647-1657.

BITTER N P, SHEPHERD J E. Stability of highly cooled hypervelocity boundary layers[J]. Journal of Fluid Mechanics, 2015, 778:586-620.

STEMMER C. Hypersonic transition investigations in a flat-plate boundary-layer flow at M =20[C ] //35th AIAA Fluid Dynamics Conference and Exhibit, Toronto, Ontario, Canada. Reston, Virigina: AIAA, 2005.

MARXEN O, IACCARINO G, MAGIN T E. Direct numerical simulations of hypersonic boundary-layer transition with finite-rate chemistry[J]. Journal of Fluid Mechanics, 2014, 755:35-49.

MORTENSEN C H, ZHONG X L. Real-gas and surface-ablation effects on hypersonic boundary-layer instability over a blunt cone[J]. AIAA Journal, 2016, 54(3):980-998.

CHANG C L, VINH H, MALIK M, et al. Hypersonic boundary-layer stability with chemical reactions using PSE[C]//28th Fluid Dynamics Conference, Snowmass Village, CO, USA. Reston, Virigina: AIAA, 1997.

ZANUS L, MIRÓ MIRÓ F, PINNA F. Nonlinear parabolized stability analysis of hypersonic flows in presence of curvature effects[C]//2018 AIAA Aerospace Sciences Meeting, Kissimmee, Florida. Reston, Virginia: AIAA, 2018.

ADAM P H, HORNUNG H G. Enthalpy effects on hypervelocity boundary-layer transition:ground test and flight data[J]. Journal of Spacecraft and Rockets, 1997, 34(5):614-619.

WADHAMS T, MACLEAN M, HOLDEN M, et al. A review of transition studies on full-scale flight vehicles at duplicated flight conditions in the LENS tunnels and comparisons with prediction methods and flight measurement[C]//48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition, Orlando, Florida. Reston, Virigina: AIAA, 2010.

GRONVALL J E, JOHNSON H B, CANDLER G V. Boundary-layer stability analysis of the high enthalpy shock tunnel transition experiments[J]. Journal of Spacecraft and Rockets, 2014, 51(2):455-467.

GROSSIR G, PINNA F, BONUCCI G, et al. Hypersonic boundary layer transition on a 7 degree half-angle cone at Mach 10[C]//7th AIAA Theoretical Fluid Mechanics Conference, Atlanta, GA. Reston, Virginia: AIAA, 2014.

PARK C. Assessment of two-temperature kinetic model for ionizing air[J]. Journal of Thermophysics and Heat Transfer, 1987, 3(3):233-244.

WILKE C R. A viscosity equation for gas mixtures[J]. The Journal of Chemical Physics, 1950, 18(4):517-519.

BLOTTNER F G, JOHNSON M, ELLIS M. Chemically reacting viscous flow program for multi-component gas mixtures[R ] . Office of Scientific and Technical Information (OSTI), 1971. doi: 10.2172/4658539

VINCENTI W G, KRUGER C H. Introduction to Physical Gas Dynamics[M]. John Wiley and Sons, 1967.

MILLIKAN R C, WHITE D R. Systematics of vibrational relaxation[J]. The Journal of Chemical Physics, 1963, 39(12):3209-3213.

MCBRIDE B J, HEIMEL S, EHLERS J, et al. Thermodynamic properties to 6000 K for 210 substances involving the first 18 elements. NASA SP-3001[R]. NASA Lewis Research Center, 1963.

PARK C, JAFFE R L, PARTRIDGE H. Chemical-kinetic parameters of hyperbolic earth entry[J]. Journal of Thermophysics and Heat Transfer, 2001, 15(1):76-90.

BLOTTNER F G. Chemical nonequilibrium boundary layer[J]. Journal of Spacecraft and Rockets, 2003, 40(5):810-818.

MIRÓ MIRÓ F, PINNA F, BEYAK E S, et al. Diffusion and chemical non-equilibrium effects on hypersonic boundary-layer stability[C]//2018 AIAA Aerospace Sciences Meeting, Kissimmee, Florida. Reston, Virginia: AIAA, 2018.

MACK L M. Boundary-layer linear stability theory[R]. AGARD Report No. 709, 1984.

BITTER N P. Stability of hypervelocity boundary layers[D]. California Institute of Technology, 2015.

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