Volume 40 Issue 9
Sep.  2025
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LIU Yongping, KOU Xiping, ZHA Jun, et al. Isentropic flow characteristics of heavy gas medium[J]. Journal of Aerospace Power, 2025, 40(9):20230421 doi: 10.13224/j.cnki.jasp.20230421
Citation: LIU Yongping, KOU Xiping, ZHA Jun, et al. Isentropic flow characteristics of heavy gas medium[J]. Journal of Aerospace Power, 2025, 40(9):20230421 doi: 10.13224/j.cnki.jasp.20230421

Isentropic flow characteristics of heavy gas medium

doi: 10.13224/j.cnki.jasp.20230421
  • Received Date: 2023-06-26
    Available Online: 2025-07-01
  • In order to study the compressible flow field characteristics of heavy gas medium in high-speed wind tunnel and its related influencing factors, the real gas effect of heavy gas medium was considered, and based on one-dimensional isentropic flow theory, the flow field parameters for a specified set of free-stream Mach numbers under the given total pressure and total temperature were calculated under wind tunnel typical operating conditions. The calculation results showed that the gas compression factor Z was close to 1 for heavy gas tetrafluoroethane (R-134a) and sulfur hexafluoride (SF6) at higher total temperature, and the specific heat ratio γ was basically constant at certain total temperature and total pressure within the range of free-stream Mach number from 0.3 to 1.3, and it was possible to consider the heavy gas both thermally and calorically perfect. Under the certain condition of total temperature and total pressure, the Mach number deviation obtained by treating heavy gas both thermally and calorically perfect was less than 0.3%, which met the requirements of wind tunnel Mach number control. In view of the high-speed flow around the airfoil, the analysis of flow field parameters of isentropic flow between heavy gas and air showed that the large difference of static temperature of flow field may cause the deviation of wind tunnel test data between heavy gas and air, and then the test data obtained under heavy gas shall be transformed accordingly. This could provide a basic support for subsequent research on aerodynamic characteristics of aircraft in heavy gas medium and the development of aerodynamic data correction methods.

     

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