Gas Dynamic Design and Numerical Study of Supersonic Circuit of Wind Tunnel

Authors: Rtischeva A.S. Published: 27.03.2021
Published in issue: #1(136)/2021  

DOI: 10.18698/0236-3941-2021-1-68-84

Category: Aviation and Rocket-Space Engineering | Chapter: Aerodynamics and Heat Transfer Processes in Aircrafts  
Keywords: wind tunnel, nozzle, test section, diffusor, numerical simulation

For an advanced trisonic wind tunnel of a straight-flow type with a test section size of 1.2 × 1.2, intended for ground tests of rocket-space and aviation aircraft models, we implemented a gas-dynamic design of the circuit and did numerical simulation of the flow for the main supersonic regimes (M = 2, M = 4). The gas-dynamic design of the wind tunnel circuit was carried out on the basis of techniques developed at TsAGI and operating experience of existing facilities. The study considers both traditional configurations of the duct with the bending of the walls of all elements, i.e., nozzle, test section and diffuser in the XY plane, and alternative design developments with the bending of the diffuser walls in the XZ plane. When carrying out numerical studies in all areas of the wind tunnel, the ANSYS Fluent software package was used to solve the Navier --- Stokes equations for viscous and heat-conducting air using the turbulence model, i.e., Spalart --- Allmaras, SST. The paper investigates the effect of the wall opening angle, compensating the increasing thickness of boundary-layer longwise displacement, on the flow characteristics; shows the possibilities of obtaining a sufficiently uniform flow with the Mach number accuracy ΔM = ± 0.005 in the area of the model, and analyzes the influence of geometric parameters and boundary conditions on the efficiency of the supersonic diffuser


[1] Drozdov S.M., Rtishcheva A.S. [Numerical study on air flow in wind tunnel circuit]. Mat. mezhdunar. konf. "Sovremennye problemy teplofiziki i energetiki". T. 1 [Proc. Int. Conf. Modern Problems of Thermal Physics and Power Engineering], 2017, vol. 1, pp. 131--132 (in Russ.).

[2] Drozdov S.M., Rtishcheva A.S. Numerical investigation of air flow in a supersonic wind tunnel. J. Phys.: Conf. Ser., 2017, vol. 891, art. 012043. DOI: https://doi.org/10.1088/1742-6596/891/1/012043

[3] Drozdov S.M., Davletkil’deev R.A., Rtishcheva A.S. Numerical and experimental investigation of air flow and heat transfer in a complete circuit of a hypersonic wind tunnel. Int. Conf. HiSST. Moscow, TsAGI, 2018.

[4] Drozdov S.M., Davletkilʼdeev R.A., Rtishcheva A.S. Numerical and experimental study of air flow and heat transfer in the complete path of a hypersonic wind tunnel. TsAGI Sc. J., 2019, vol. 50, no. 2, pp. 141--153. DOI: https://doi.org/10.1615/TsAGISciJ.2019030550

[5] Verkhovskiy V.P., Lysak I.V. Numerical method for calculation of flat supersonic adjustable nozzle contours using spline-functions. Uchenye zapiski TsAGI, 1982, vol. 13, no. 4, pp. 61--70 (in Russ.).

[6] Verkhovskiy V.P., Ryabokonʼ M.P., Kharitonov V.T. Effect of flat adjustable nozzle deviation from its theoretical contour on the distribution of Mach number in supersonic gas flow. Trudy TsAGI, 1984, no. 2208 (in Russ.).

[7] Verkhovskiy V.P. On calculations of flat supersonic contoured nozzles. Uchenye zapiski TsAGI, 1992, vol. 23, no. 4, pp. 55--63 (in Russ.).

[8] Byushgens G.S., ed. TsAGI --- osnovnye etapy nauchnoy deyatel’nosti, 1993--2003 [TsAGi: milestones of scientific activity, 1993--2003]. Moscow, FIZMATLIT Publ., 2003.

[9] Kotirov V.N., Osipov I.P., Pashchenko V.P. On forming of flat supersonic nozzle contour providing uniform flow in inlet section. Uchenye zapiski TsAGI, 1987, vol. 18, no. 3, pp. 48--56 (in Russ.).

[10] Pirumov U.G., Roslyakov G.S. Gazovaya dinamika sopel [Gas dynamics of nozzles]. Moscow, Nauka Publ., 1990.

[11] Timofeeva T.A., Chistov Yu.I. Evaluation of boundary layer displacement thickness in axisymmetric hypersonic nozzles at constant temperature of wall. Trudy TsAGI, 1972, no. 1403 (in Russ.).

[12] Kharitonov A.M. Tekhnika i metody aerofizicheskogo eksperimenta. Ch. 1. Aerodinamicheskie truby i gazodinamicheskie ustanovki [Technique and methods of aerophysical experiment. P. 1. Wind tunnels and gas dynamic facilities]. Novosibirsk, NGTU Publ., 2005.

[13] Pope A., Goin K.L. High-speed wind tunnel testing. London, John Wiley & Sons, 1965.

[14] Gorlin S.M., Slezinger I.I. Aeromekhanicheskie izmereniya (metody i pribory) [Aeromechanic measurements (methods and tools)]. Moscow, Nauka Publ., 1964.

[15] Abramovich G.N. Prikladnaya gazovaya dinamika [Applied gas dynamics]. Moscow, Nauka Publ., 1991.