Abstract
In the present paper, a plane jet issuing from a parallel supersonic nozzle into the chamber where the pressure corresponds to the constant pressure point on the shock polar related to the uniform velocity at the exit of the nozzle is investigated by the hodograph method under the transonic approximation. The analytical expression for the stream function ψis obtained in the form containing appropriate constants which are determined from the condition on the shock polar. Actually, ψ is calculated so that the shock condition is satisfied at three points on the shock polar. Using this value of ψ, the shock pattern and the velocity distribution along the axis of the jet are obtained. It is seen from these results that large variations of the flow variables occur in a comparatively narrow region downstream of the exit of the nozzle.
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