Abstract
The pressure distributions over the surfaces of simple model bodies, such as hemisphere, wedge, and cone, and the bow shock stand-off distances from these bodies are investigated in hypersonic wind tunnels with similar-in-value Mach and Reynolds numbers but considerably different flow velocities (u = 790 to 5950 m/s). These are the tunnels with an ohmic heater and electric-arc and MHD gas flow accelerators. Flow pattern visualization followed by photometering measurements are used for determining the bow shock stand-off distance. At low gas densities the method of anomalous dispersion of the sounding radiation is employed for visualizing the flow. The pressure distributions over the body surfaces and the bow shock stand-off distances are calculated from the Navier-Stokes equations and thin viscous shock layer (TVSL) theory. The measured parameter values are in agreement with those calculated from Navier-Stokes equations. For the cone and the wedge the discrepancy is within 10%.
This is a preview of subscription content, log in via an institution to check access.
Similar content being viewed by others
References
B.E. Zhestkov, A.V. Lipin, and A.P. Nikiforov, “Experimental Equipment NIO-8 for Solving the Problems of Aerodynamics and Heat Transfer at High Altitudes and Some Applied Problems,” in: All-Russian Science and Engineering Conf. “Basic Research in Hypersonic Technologies”, Vol. 2 [in Russian], TsAGI, Zhukovskii (1998), p. 563.
V.I. Alferov, O.N. Vitkovskaya, V.P. Rukavets, and G.I. Shcherbakov, “Investigation of an Aerodynamic Setup with Magnetogasdynamic Gas Flow Acceleration,” Teplofiz. Vys. Temp. 17(1), 163 (1979).
H.B. Keller and T. Cebeci, “Accurate Numerical Method for Boundary-Layer Flows. II. Two-Dimensional Turbulent Flow,” AIAA J. 10, 1193 (1972).
V.I. Alferov, A.S. Bushmin, and L.M. Dmitriev, “Methods of Experimental Investigation of Thermally Nonequilibrium Supersonic Flows,” in: Collection of Studies on Measuring and Computational Systems for Investigating Aerodynamics, Dynamics, and Strength of Flight Vehicles. Issue 1847 [in Russian], TsAGI, Moscow (1977), p. 89.
A.S. Bushmin and A.A. Orlov, “Using a Rearranged Dye Laser for Investigations in High-Velocity Gas Flows,” Tepl. Vys. Temp. 14, 911 (1976).
H.K. Cheng, “Hypersonic Shock-Layer Theory of the Stagnation Region at Low Reynolds Number,” in: Proc. Heat Transfer Fluid Mech., Stanford (1961), p. 161.
Y.B. Zel’dovich and Y.P. Raizer, Physics of Shock Waves and High Temperature Hydrodynamic Phenomena. Vols. 1 and 2, Academic Press, San Diego (1967).
S.W. Kang and M.C. Dunn, “Theoretical and Measured Electron-Density Distribution for the RAM Vehicle at High Altitudes,” AIAA Paper No. 689 (1972).
P.E. Babikov and I.V. Yegorov, “On One Version of the Adaptive Grid Generation to Solve Evolution Problems,” in: Proc. Soviet Union-Japan SCFD. Vol. 2, Khabarovsk (1988), p. 222.
I.V. Egorov and O.L. Zaitsev, “An Approach to the Numerical Solution of the Two-Dimensional Navier-Stokes Equations Using the Shock Capturing Technique,” Zh. Vychisl. Mat. Mat. Fiz. 31, 286 (1991).
V.I. Alferov, A.S. Bushmin, and A.A. Shinelev, “On the Possibility of Using Optical Methods for Determining the Hypersonic Flow Structure,” Teplofiz. Vys. Temp. 45, 422 (2007).
Author information
Authors and Affiliations
Corresponding author
Additional information
Original Russian Text © V.I. Alferov, A.S. Bushmin, I.V. Egorov, 2015, published in Izvestiya Rossiiskoi Akademii Nauk, Mekhanika Zhidkosti i Gaza, 2015, Vol. 50, No. 1, pp. 120–129.
Rights and permissions
About this article
Cite this article
Alferov, V.I., Bushmin, A.S. & Egorov, I.V. Experimental investigation of flow past simple model bodies in hypersonic wind tunnels at similar values of the Mach and Reynolds numbers but at different physical flow velocities. Fluid Dyn 50, 109–117 (2015). https://doi.org/10.1134/S0015462815010123
Received:
Published:
Issue Date:
DOI: https://doi.org/10.1134/S0015462815010123