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 else somewhat further 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 a correction is derived in the form of an inner solution for a small region immediately behind the shock. The resulting solution exhibits the characteristics which are expected at the intersection of a normal shock wave and a curved wall. An extension to axisymmetric flow is also given. (Modified author abstract)
Document Details
- Document Type
- Technical Report
- Publication Date
- Jul 01, 1974
- Accession Number
- AD0785283
Entities
People
- A. F. Messiter
- T. C. Adamson
Organizations
- Purdue University