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The flow field of a sonic jet exhausting counter to a supersonic airstream has been investigated theoretically and experimentally. An inviscid analysis shows the shock layer thickness and the position of the outer and inner shocks to be a function of free stream Mach number, jet reservior pressure, free stream Pitot pressure, and orifice size. The predicted inner shock position agrees with previous data in the continuum. The experiments were conducted in a Mach 3 low-density wind tunnel at free stream Re/l == 2.9 to 31.5 per cm and p0i/p′0∞ 10 to 104. The experimental results in the transition regime show the orifice to outer shock distance is greater than the predicted inviscid value.
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Cassanova et al. (1969) studied this question.
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