Nonlinear wave interactions in a transitional hypersonic boundary layer

被引:9
|
作者
Zhang, Chuanhong [1 ,2 ,3 ]
Shi, Zhiwei [1 ,3 ]
机构
[1] Nanjing Univ Aeronaut & Astronaut, Coll Aerosp Engn, 29 Yudao St, Nanjing 210016, Jiangsu, Peoples R China
[2] Peking Univ, Coll Engn, State Key Lab Turbulence & Complex Syst, 5 Yiheyuan Rd, Beijing 100871, Peoples R China
[3] Nanjing Univ Aeronaut & Astronaut, Key Lab Unsteady Aerodynam & Flow Control, Minist Ind & Informat Technol, 29 Yudao St, Nanjing 210016, Jiangsu, Peoples R China
基金
中国国家自然科学基金;
关键词
SPECTRAL DYNAMICS; 2ND MODE; EVOLUTION; SIMULATIONS; INSTABILITY;
D O I
10.1063/5.0120425
中图分类号
O3 [力学];
学科分类号
08 ; 0801 ;
摘要
The linear and nonlinear evolutions and breakdown of the second modes in hypersonic boundary layers (HBLs) on a flared cone are investigated using Rayleigh-scattering flow visualization and fast-response pressure sensors. Based on two spatially separated pressure signals, cross-bicoherence analysis that permits the distinction of sum- and difference-interactions is utilized to identify the nonlinear interactions. In addition, the visualization temporal and spatial resolution allows fine flow features to be captured to provide additional flow information. Amplitude correlation technique is used to estimate the nonlinear energy transfer between the modes. Our results show that nonlinear interactions between the second mode and the low-frequency wave contribute to the growth of the low-frequency wave, and the difference interactions between the second mode and its first harmonic play a dominant role in modulating the waves in the overall transition process. Amplitude correlation analysis reveals that the spectral energy is nonlinearly transferred from the second mode into its first harmonic and into low-frequency wave, in agreement with the cross-bicoherence analysis. The amplitude modulation of the second mode caused by the difference interaction between the second mode and its first harmonic will reduce the propagation speed of the second mode. However, at the final breakdown stage, this difference interaction vanishes, and the second-mode propagation velocity recovers quickly. Since the frequency of the second mode keeps almost unchanged over the entire transition process, a higher propagation velocity will result in a larger wavelength, indicating an elongation and deformation of the second mode. Eventually, the difference interaction between the second mode and the low-frequency wave accompanying the energy transfer from the second mode to low-frequency waves leads to the final breakdown of the HBLs into a turbulent state. Published under an exclusive license by AIP Publishing.
引用
收藏
页数:13
相关论文
共 50 条
  • [31] INTERACTIONS WITHIN LAMINAR HYPERSONIC BOUNDARY LAYER
    JOHNSON, RH
    AIAA JOURNAL, 1966, 4 (12) : 2245 - &
  • [32] Transitional Shock-Wave/Boundary-Layer Interactions in Intakes at Incidence
    Makuni, Tafara E.
    Kalsi, Hardeep S.
    Tucker, Paul G.
    Babinsky, Holger
    ADVANCES IN SIMULATION OF WING AND NACELLE STALL, 2016, 131 : 323 - 333
  • [33] Transitional shock wave - Boundary layer interaction over a cone-flare model at hypersonic conditions
    Asma, CO
    Paris, S
    Tapsoba, MSD
    Fletcher, DG
    4TH EUROPEAN SYMPOSIUM ON AEROTHERMODYNAMICS FOR SPACE VEHICLES, PROCEEDINGS, 2002, 487 : 725 - 731
  • [34] Multi-scale study of the transitional shock-wave boundary layer interaction in hypersonic flow
    Lugrin, Mathieu
    Beneddine, Samir
    Garnier, Eric
    Bur, Reynald
    THEORETICAL AND COMPUTATIONAL FLUID DYNAMICS, 2022, 36 (02) : 277 - 302
  • [35] Multi-scale study of the transitional shock-wave boundary layer interaction in hypersonic flow
    Mathieu Lugrin
    Samir Beneddine
    Eric Garnier
    Reynald Bur
    Theoretical and Computational Fluid Dynamics, 2022, 36 : 277 - 302
  • [36] Control of Severe Shock-Wave/Boundary-Layer Interactions in Hypersonic Inlets
    Xie, Wen-Zhong
    Wu, Zhong-Ming
    Yu, An-Yuan
    Guo, Shengmin
    JOURNAL OF PROPULSION AND POWER, 2018, 34 (03) : 614 - 623
  • [37] Numerical studies on uncontrolled and controlled shock wave/boundary layer interactions in hypersonic intake
    Bharghava D.S.N.
    Mali A.K.
    Jana T.
    Kaushik M.
    Aerospace Systems, 2024, 7 (03) : 539 - 557
  • [38] Investigation of supersonic/hypersonic shock-wave/boundary-layer interactions (SBLIs)
    Bura, RO
    Roberts, GT
    Yao, YF
    Sandham, ND
    SHOCK WAVES, VOLS 1 AND 2, PROCEEDINGS, 2005, : 695 - 700
  • [39] Expansion corner effects on hypersonic shock wave turbulent boundary-layer interactions
    White, ME
    Ault, DA
    JOURNAL OF PROPULSION AND POWER, 1996, 12 (06) : 1169 - 1173
  • [40] Nonlinear wave processes in a hypersonic shock layer
    Maslov, A. A.
    Poplavskaya, T. V.
    Tsyryul'nikov, I. S.
    FLUID DYNAMICS, 2010, 45 (04) : 552 - 558