Drozdov S.M., Davletkildeev R.A., Rtischeva A.S.
DOI Number XXX-YYY-ZZZ
Conference Number HiSST 2018_640800
This work presents numerical and experimental investigation of high-enthalpy real air flow structure in the complete circuit of TsAGI T-117 hypersonic wind tunnel with account for heat transfer processes in the air cooler and at wind tunnel walls. In the numerical simulation, wind tunnel circuit was modeled as a sequence of axisymmetric segments: a prechamber, a shaped nozzle, a simplified test section, a supersonic diffuser, a chamber preceding the cooler, a semipermeable cooler segment, a chamber after the cooler, and a fragment of the gas exhaust system. In all segments, axisymmetric Navier-Stokes equations for viscous heat-conducting air with a turbulence model were solved using ANSYS Fluent software. Real-gas properties of air were modeled in assumption of equilibrium excitation of О2 and N2 vibration modes. The most challenging segment for numerical modeling is the cooler which consists of 1797 individually water-cooled tubes. Two models of air flow through the cooler are considered. The first is the simplified “Darcy” model, in which the cooler is represented as a porous medium. In the second model, “slot channels”, the air cooler segment is represented by a set of axisymmetric channels, and convective heat exchange with the cooling water is assumed on their exterior. Results of numerical simulation of gas dynamics in the complete circuit of T-117 wind tunnel and heat transfer processes in the air cooler and at wind tunnel walls, at regimes with Mach number M=7.5 and M=10.5 in the test section, are analyzed in this work. Comparison is made between simulation results and experimental data.