On the flow near a weak shock wave downstream of a nozzle throat
Abstract
In a transonic nozzle flow for which the velocity is slightly supersonic in some neighborhood of the nozzle throat, a shock wave may be present either very close to the throat or somewhat farther downstream. In the latter case, relatively simple series solutions in general provide an asymptotic description of the fluid motion except very close to the shock wave. These outer solutions are reviewed for symmetric two dimensional flow and it is shown that the shockwave jump conditions are not satisfied. A correction is then derived in the form of an inner solution for a small region immediately behind the shock. The resulting solution exhibits the singularities in pressure gradient, streamline curvature, and shock wave curvature which are expected to occur at the intersection of a normal shock wave and a curved wall. An extension to axisymmetric flow is also given.
 Publication:

NASA STI/Recon Technical Report N
 Pub Date:
 July 1974
 Bibcode:
 1974STIN...7512257M
 Keywords:

 Flow Distribution;
 Nozzle Flow;
 Pressure Gradients;
 Shock Waves;
 Transonic Flow;
 Flow Equations;
 Numerical Analysis;
 Stream Functions (Fluids);
 Two Dimensional Flow;
 Fluid Mechanics and Heat Transfer