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Experimental investigation of the recovery of the total pressure in a hypersonic wind tunnel with conical and profiled nozzles

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Abstract

Measurements have been made of the coefficient of recovery ν of the total pressure of a gas flow exhausting from axisymmetric and conical profiled hypersonic nozzles into a cylindrical channel of diameter equal to or greater than the nozzle exit and also in the presence of an Eiffel chamber. The experiments were made at Mach numbers M = 4.83−12.4 in the isentropic core. It is shown that the values of ν differ slightly (by ∼5%) from the corresponding value for a normal shock wave at the number Mϕ determined for a onedimensional flow by the ratio of the area of the cylindrical channel to the area of the critical section of the nozzle.

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Literature cited

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    I. I. Mezhirov, “Losses of the total pressure in a hypersonic wind tunnel,” Inzh. Zh.,5, 243 (1965).

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    I. I. Mezhirov and Yu. I. Chistov, “Investigation of the recovery of the total pressure in the flow behind hypersonic nozzles,” Uch. Zap. TsAGI,12, 110 (1981).

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    G. N. Abramovich, Applied Gas Dynamics [in Russian], Nauka, Moscow (1976), p. 888.

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    O. V. Lyzhin and I. I. Mezhirov, “Averaging of the total pressure of a nonuniform gas flow,” Uch. Zap. TsAGI,11, 60 (1980).

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Translated from Izvestiya Akademii Nauk SSSR, Mekhanika Zhidkosti i Gaza, No. 1, pp. 170–173, January–February, 1984.

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Mezhirov, I.I., Chistov, Y.I. Experimental investigation of the recovery of the total pressure in a hypersonic wind tunnel with conical and profiled nozzles. Fluid Dyn 19, 150–153 (1984). https://doi.org/10.1007/BF01090926

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Keywords

  • Shock Wave
  • Experimental Investigation
  • Mach Number
  • Wind Tunnel
  • Total Pressure