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
  • [1] Hypersonic shock wave transitional boundary layer interactions - A review
    Knight, Doyle
    Mortazavi, Mahsa
    ACTA ASTRONAUTICA, 2018, 151 : 296 - 317
  • [2] Shock wave/transitional boundary-layer interactions in hypersonic flow
    Benay, R.
    Chanetz, B.
    Mangin, B.
    Vandomme, L.
    Perraud, J.
    AIAA JOURNAL, 2006, 44 (06) : 1243 - 1254
  • [3] Transitional shock-wave/boundary-layer interactions in hypersonic flow
    Sandham, N. D.
    Schuelein, E.
    Wagner, A.
    Willems, S.
    Steelant, J.
    JOURNAL OF FLUID MECHANICS, 2014, 752 : 349 - 382
  • [4] Nonlinear interactions in a hypersonic boundary layer
    Zhang, Chuanhong
    Shi, Zhiwei
    AIP ADVANCES, 2021, 11 (03)
  • [5] Nonlinear interactions in the hypersonic boundary layer on the permeable wall
    Zhu, Wenkai
    Chen, Xi
    Zhu, Yiding
    Lee, Cunbiao
    PHYSICS OF FLUIDS, 2020, 32 (10)
  • [6] Shock wave boundary layer interactions in hypersonic flows
    John, Bibin
    Kulkarni, Vinayak N.
    Natarajan, Ganesh
    INTERNATIONAL JOURNAL OF HEAT AND MASS TRANSFER, 2014, 70 : 81 - 90
  • [7] Double Peak-Heating in Hypersonic Transitional Shock-Wave/Boundary-Layer Interactions
    Currao, Gaetano M. D.
    Chen, Wen-Lih
    AIAA JOURNAL, 2021, 60 (04) : 2051 - 2059
  • [8] Unsteady Characteristics and Enhanced Determination of Reattachment for Hypersonic Transitional Shock-Wave/Boundary-Layer Interactions
    Davami, Jonathan
    Juliano, Thomas J.
    AIAA AVIATION FORUM AND ASCEND 2024, 2024,
  • [9] Hypersonic Transitional Shock-Wave-Boundary-Layer Interaction on a Flat Plate
    Currao, Gaetano M. D.
    Choudhury, Rishabh
    Gai, Sudhir L.
    Neely, Andrew J.
    Buttsworth, David R.
    AIAA JOURNAL, 2020, 58 (02) : 814 - 829
  • [10] Tunnel Noise Effects on Hypersonic Cylinder-Induced Transitional Shock-Wave/Boundary-Layer Interactions
    Leidy, Andrew N.
    Neel, Ian T.
    Schmisseur, John D.
    Tichenort, Nathan R.
    Bowerso, Rodney D. W.
    AIAA JOURNAL, 2021, 59 (07) : 2357 - 2367