Accession Number : AD0785283

Title :   On the Flow Near a Weak Shock Wave Downstream of a Nozzle Throat,

Descriptive Note : Technical rept.,


Personal Author(s) : Messiter,A. F. ; Adamson,T. C.

Report Date : JUL 1974

Pagination or Media Count : 27

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)

Descriptors :   *Transonic nozzles, *Supersonic characteristics, *Shock waves, *Nozzle throats, Mathematical models, Series(Mathematics), Two dimensional flow, Corrections, Nozzle gas flow

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE