Experimental research on characteristics of pressure and heat flux fluctuation in hypersonic cone boundary layer

LI Qiang; WAN Bingbing; YANG Kai; ZHU Tao

doi:10.7527/S1000-6893.2020.24956

ACTA AERONAUTICAET ASTRONAUTICA SINICA >

2022 , Vol. 43 >Issue 2: 124956 - 124956

DOI: https://doi.org/10.7527/S1000-6893.2020.24956

Fluid Mechanics and Flight Mechanics

Experimental research on characteristics of pressure and heat flux fluctuation in hypersonic cone boundary layer

LI Qiang ,
WAN Bingbing ,
YANG Kai ,
ZHU Tao

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1. Computational Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China;
2. Hypervelocity Aerodynamics Institute, China Aerodynamics Research and Development Center, Mianyang 621000, China

Received date: 2020-11-09

Revised date: 2020-12-05

Online published: 2021-01-08

Supported by

National Key Research and Development Program of China(2019YFA0405300)

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Abstract

High-frequency heat flux fluctuation is important in shock tunnel tests for experimental investigation of hypersonic boundary layer transition. A cone model is applied to test the self-innovated Atomic Layer Thermopile (ALTP) heat-flux sensors under the experimental condition of Mach number 10 with the unit Reynolds number being 1.2×10⁷/m, 4.7×10⁶/m and 2.4×10⁶/m, respectively, in the Ø2 m shock tunnel (FD-14A) of China Aerodynamics Research and Development Center. The tests obtained the spectrum characteristics of the heat flux and pressure fluctuation in the cone model boundary layer under different flow conditions, and through comparison with the high-frequency pressure fluctuation and N factor from linear stability theory computation, the spectrum response capability of the self-innovated ALTP heat-flux sensor is confirmed, indicating its applicability to the research on hypersonic boundary layer transition. The test results show that the heat flux fluctuation has a different spectrum characteristic from that of the pressure fluctuation; the pressure fluctuation energy distribution is relatively uniform under turbulent conditions, while the heat flux fluctuation energy decays more obviously with frequency increase; compared to the pressure fluctuation, the heat flux fluctuation signal is less susceptible to interference; the peak spectrum of the second mode wave of the heat flux fluctuation became prominent earlier than that of the pressure fluctuation in the flow field of Mach number 10 with the unit Reynolds number 2.4×10⁶/m.

Key words： hypersonic boundary layer transition; shock tunnel; high frequency fluctuation pressure; high frequency fluctuation heat flux; linear stability

Cite this article

LI Qiang , WAN Bingbing , YANG Kai , ZHU Tao . Experimental research on characteristics of pressure and heat flux fluctuation in hypersonic cone boundary layer[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2022 , 43(2) : 124956 -124956 . DOI: 10.7527/S1000-6893.2020.24956

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