Effect of wall temperature on stability and transition of hypersonic boundary layer on a blunt delta wing

MA Yilei; YU Ping; YAO Shiyong

doi:10.7638/kqdlxxb-2018.0235

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Effect of wall temperature on stability and transition of hypersonic boundary layer on a blunt delta wing

更新时间：2026-05-28

- Effect of wall temperature on stability and transition of hypersonic boundary layer on a blunt delta wing
- Vol. 38, Issue 6, Pages: 1017-1026(2020)
- 作者机构：
  
  空间物理重点实验室,北京,100076
- 作者简介：
- 基金信息：
- DOI：10.7638/kqdlxxb-2018.0235
  CLC： O357.4
- Published：2020
- 稿件说明：
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马祎蕾, 余平, 姚世勇. 壁温对钝三角翼边界层稳定性及转捩影响[J]. 空气动力学学报, 2020, 38(6): 1017-1026.

MA Yilei, YU Ping, YAO Shiyong. Effect of wall temperature on stability and transition of hypersonic boundary layer on a blunt delta wing[J]. 2020, 38(6): 1017-1026.
马祎蕾, 余平, 姚世勇. 壁温对钝三角翼边界层稳定性及转捩影响[J]. 空气动力学学报, 2020, 38(6): 1017-1026. DOI： 10.7638/kqdlxxb-2018.0235.

MA Yilei, YU Ping, YAO Shiyong. Effect of wall temperature on stability and transition of hypersonic boundary layer on a blunt delta wing[J]. 2020, 38(6): 1017-1026. DOI： 10.7638/kqdlxxb-2018.0235.

摘要

选择典型的高超声速流动条件，基于线性稳定性理论研究了不同壁温条件对典型大后掠角平板钝三角翼外形高超声速三维边界层流动稳定性及转捩的影响。研究表明，壁温比的增加促进横流和第一模态波的增长，第二模态波受到抑制，钝三角翼表面

值分布的变化呈现随壁温比增加先减小后增大的特点，预示在高壁温比下（绝热壁附近，约0.8）将出现转捩反转；转捩反转的内在机理在于壁温比对不同模态彼此相反的影响规律以及在不同位置不同的影响量值，导致在低壁温比区壁温比的增加主要影响第二模态，引起转捩延迟，而在高壁温比区壁温比的增加对第一模态的影响超过了对第二模态的影响，转而造成转捩前移。

Abstract

Effects of different wall temperature conditions on stabilities and transition of three-dimensional hypersonic boundary layer over a flat plate blunt delta wing with large sweep angle are studied by using linear stability theory (LST) analysis. An adiabatic wall case and three isothermal wall cases with wall-to-total temperature ratios of 0.357

0.714

which are lower than adiabatic case ratio

and 0.952

which is higher than adiabatic case ratio

are considered. The results indicate that the increase of wall-to-total temperature ratio promotes the growth of cross mode and T-S mode disturbances

while suppressing second mode disturbances

which leads to a transition reversal

the

-factor decreases

first and then increases at high temperature ratio (about 0.8 near adiabatic wall condition). The mechanism of the transition reversal is the opposite influence tendency of temperature ratio on different disturbance modes

and the different influence degrees at different locations of delta wing. When there is a low temperature ratio

the increase of ratio mainly affects the second mode near center line of delta wing

resulting in the delay of transition; however

when the ratio is high

it affects cross mode and T-S mode along leading edge more than the second mode near center

which in turn causes the transition to move forward.

关键词

Keywords

references

CHEN J Q, TU G H, ZHANG Y F, et al. Hypersonic 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 layertransition[J]. Acta Aerodynamica Sinica, 2018, 36(2):183-195.(in Chinese)

YU P, DUAN Y, CHEN J. Some aerodynamic issues in hypersonic flight[J]. Acta Aeronautica et Astronautica Sinica, 2015, 36(1):7-23.(in Chinese)

BUSHNELL D M, YIP L P, YAO C S, et al. Reynolds number influences in aeronautics[R]. NASA TM-107730, 1993.

FEDOROV A V. Prediction and control of laminar-turbulent transition in high-speed boundary-layer flows[J]. Procedia IUTAM, 2015, 14:3-14. DOI:10.1016/j.piutam.2015.03.017

CHAPMAN G T. Transition of the laminar boundary layer on a delta wing with 74° sweep in free flight at Mach numbers from 2.8 to 5.3[R].NASA TN-D-1066, 1961.

STETSON K, THOMPSON E, DONALDSON J, et al. Laminar boundary layer stability experiments on a cone at Mach 8. V-Tests with a cooled model[C ] //Proc of the 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, Buffalo, NY, USA. Reston, Virigina: AIAA, 1989. AIAA-89-1895. DOI: 10.2514/6.1989-1895

MALIK M. Prediction and control of transition in hypersonic boundary layers[C ] //Proc of the 19th AIAA, Fluid Dynamics, Plasma Dynamics, and Lasers Conference, Honolulu, HI, USA. Reston, Virigina: AIAA, 1987. AIAA-87-1414. DOI: 10.2514/6.1987-1414

GASPERAS G. Effect of wall temperature distribution on the stability of the compressible boundary layer[C ] //Proc of the 20th Fluid Dynamics, Plasma Dynamics and Lasers Conference, Buffalo, NY, USA. Reston, Virigina: AIAA, 1989. AIAA-89-1894. DOI: 10.2514/6.1989-1894

SHANG Q, CHEN L, LI X, et al. Wall temperature effect on transition flow and separated flow in hypersonic flow around a blunt double wedge[J]. Acta Aeronautica et Astronautica Sinica, 2014, 35(11):2958-2969.(in Chinese)

SU C H, ZHOU H. Stability analysis and transition prediction of hypersonic boundary layer over a blunt cone with small nose bluntness at zero angle ofattack[J]. Applied Mathematics and Mechanics, 2007, 28(5):505-513.(in Chinese)

CAO W. A study of the transition prediction of hypersonic boundary layer on plane and wedgeflow[J]. Acta Aerodynamica Sinica, 2009, 27(5):516-523.(in Chinese)

LIU Z Y, YANG W B, SHEN Q. Investigation on correlation between wind tunnel and flight test data for boundary layer transition[C ] //Proc of the AIAA Flight Testing Conference, Washington, D.C. Reston, Virginia: AIAA, 2016. AIAA 2016-3980. DOI: 10.2514/6.2016-3980

LIANG X, LI X L, FU D X, et al. Effects of wall temperature on boundary layer stability over a blunt cone at Mach 7.99[J]. Computers Fluids, 2010, 39(2):359-371. DOI:10.1016/j.compfluid.2009.09.015

WANG Z Q, TANG X J, MENG X N, et al. Effect of wall temperature on the stability of hypersonic boundary layer over a blunt wedge under the action of pulse wave in incoming stream[J]. Journal of Astronautics, 2014, 35(4):481-490.(in Chinese)

EPPINK J, WLEZIEN R. Data analysis for the NASA/Boeing hybrid laminar flow control crossflow experiment[C ] //Proc of the 41st AIAA Fluid Dynamics Conference and Exhibit, Honolulu, Hawaii. Reston, Virigina: AIAA, 2011. AIAA 2011-3879. DOI: 10.2514/6.2011-3879

ZHOU H, ZHAO G F. Hydrodynamic stability[M]. Beijing:National Defense Industry Press, 2004. (in Chinese)

CEBECI T, STEWARTSON K. On stability and transition in three-dimensional flows[J]. AIAA Journal, 1980, 18(4):398-405. DOI:10.2514/3.50772

TANG D B. Boundary layer transition[M]. Beijing:Science Press, 2015.(in Chinese)

LI F, CHOUDHARI M, CHANG C L, et al. Stability analysis for HIFiRE experiments[C ] //Proc of the 42nd AIAA Fluid Dynamics Conference and Exhibit, New Orleans, Louisiana. Reston, Virigina: AIAA, 2012. AIAA 2012-2961. DOI: 10.2514/6.2012-2961

BRAZHKO V N, VAGANOV A V, KOVALEVA N A, et al. Experimental investigation at Mach number M =7.5 of aerodynamic heating and laminar-turbulent transition on blunt delta wing[C ] //ICMAR 2008.

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