Test of aero-heating in hypersonic non-equilibrium flow and numerical simulation study

Nie, Chunsheng; Liu, Yu; Huang, Jiandong; Miao, Wenbo

doi:10.1360/n092017-00311

Cited by 1 publication

(2 citation statements)

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“…The catalytic characteristics of surface materials have a significant effect on the aerodynamic heating of nonequilibrium flow [2,3]. In the arc-heated wind tunnel test, if the catalytic characteristic of the heat flux sensor is quite different from that of the test model, the measured heat flux will be inaccurate [4].…”

Section: Introductionmentioning

confidence: 99%

“…It shows that numerical simulation can provide greater insight into the operating characteristics and capabilities of the arc-heated facility and optimize the test simulation method early in the planning process. In view of the influence of catalytic characteristics on the surface aerodynamic heating, Nie et al [3] carried out the test of the spherical cylinder model in the arc-heated wind tunnel and the numerical simulation of the test flowfield. The results show that the difference between test data and numerical simulation results for the fully catalytic wall is larger than that for the noncatalytic wall.…”

Section: Introductionmentioning

confidence: 99%

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Study on the Simulation Method of the Ground Test in the Arc-Heated Wind Tunnel

Luo

Yang

Liang

et al. 2020

International Journal of Aerospace Engineering

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To analyze the effectiveness of the thermal assessment test, the simulation method of the ground test in the arc-heated wind tunnel is studied. Based on the solution of the thermochemical nonequilibrium Navier-Stokes equations, the flowfield around the spherical cylinder is simulated in the flight and ground test conditions, and the difference in the high enthalpy flowfield between the flight and ground test conditions is investigated. The flight parameters and ground test conditions are selected according to the criterion that the total enthalpy and the stagnation point heat flux of the fully catalytic cold wall (calibrated heat flux) are similar. The flowfield for different temperature boundaries and different catalytic walls is solved under the same free stream conditions, and the stagnation point heat flux and oxygen atom mass fraction are compared and analyzed. It is found that the heat flux on the fully catalytic wall for the radiation balance temperature boundary in the ground test is lower than that in the corresponding flight condition, but the difference is not obvious on the noncatalytic wall. In addition, the oxygen atom mass fraction after the shock wave in the ground test is higher than that in the corresponding flight condition. To make the stagnation point heat flux and oxygen atom mass fraction after the shock wave similar to those of the flight, the simulation method of the arc-heated wind tunnel test needs to be adjusted.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%