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