Abstract
The pressure distribution on the nozzle wall near the exit cross section was studied experimentally for different incalculability factors. “Damping lengths” and internal pressure profiles in response to increases in the pressure drop across the shock discontinuity were determined up to a value close to the detachment value, for Mach numbers M=2 to 3.5.
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Literature cited
G. I. Petrov, V. Ya. Likhushin, I. P. Nekrasov, and L. M. Sorkin, Trudy TsIAM, No. 224, Oborongiz (1952).
G. Gedd, Mechanics, No. 5 [Russian translation], IL (1959).
Additional information
Translated from Inzhenerno-Fizicheskii Zhurnal, Vol. 18, No. 2, pp. 233–236, February, 1970.
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Timoshin, A.N. Investigation of flow pattern near supersonic nozzle exit section at different incalculability factors. Journal of Engineering Physics 18, 167–169 (1970). https://doi.org/10.1007/BF00828006
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DOI: https://doi.org/10.1007/BF00828006