Abstract
An investigation has been made in an aerodynamic shock tube, with M=8, of the diffuser starting with variable Reynolds numbers, and its throttle characteristics have been recorded. The results obtained enable conclusions to be made regarding the possibility of investigating diffusers in such types of tubes. In [1] the possibility of, in principle, determining the throat starting of a diffuser in an aerodynamic shock tube, and the time to establish flow in the diffuser channel, which was ∼300 μsec, was measured. This paper is devoted to the further investigation of diffuser operation with variable Reynolds numbers, and to determining the throttle characteristics, in particular, the total pressure reduction coefficient.
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Literature Cited
V. M. Anufriev, G. I. Kozlov, and D. I. Roitenburg, “Use of aerodynamic shock tubes to investigate diffusers,” Izv. Akad. Nauk SSSR, Mekhan. Zhidk. i Gaza, No. 2 (1969).
B. D. Khenshell, “Some aspects of using shock tubes in aerodynamic investigations,” in: Shock Tubes [Russian translation], IL, Moscow (1962).
B. V. Orlov, G. Yu. Mazing, A. L. Reidel', M. N. Stepanov, and Yu. I. Topcheev, Design Basis of Direct Flow Rocket Engines for Pilotless Aircraft [in Russian], Mashinostroenie, Moscow (1967).
Additional information
Moscow. Translated from Izvestiya Akademii Nauk SSSR, mekhanika Zhidkosti i Gaza, No. 1, pp. 156–161, January–February, 1972.
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Anufriev, V.M., Kozlov, G.I. & Roitenburg, D.I. Investigation of diffuser characteristics in an aerodynamic shock tube. Fluid Dyn 7, 142–146 (1972). https://doi.org/10.1007/BF01205381
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DOI: https://doi.org/10.1007/BF01205381