Accession Number:

ADA209689

Title:

A Method for Calculating Asymmetric Flow Through Nozzles

Descriptive Note:

Final rept. Jan-Aug 1988

Corporate Author:

AEROSPACE CORP EL SEGUNDO CA ENGINEERING GROUP

Personal Author(s):

Report Date:

1989-01-01

Pagination or Media Count:

28.0

Abstract:

The asymmetric steady-state, inviscous, adiabatic flow of a perfect gas through a subsonicsupersonic nozzle is considered. The nozzle itself is either of rectangular cross section or is axisymmetric. A first-order small asymmetry induced by an entrance flow which is oblique to the nozzle axis and has a transverse pressure gradient is allowed. The cross section of the nozzle is assumed to vary only slowly as a function of the axial distance the case considered here is therefore an extension of the well-known theory of the quasi- one-dimensional flow of a perfect gas treated in standard textbooks. An integral method is used to obtain approximate results. The method is simple, yet in a test case supersonic flow at an angle of attack through a rectangular channel where the exact first-order result is known, a comparison shows surprisingly good agreement. Numerical results are tabulated for axisymmetric nozzles with polynomial Mach number dependence.

Subject Categories:

  • Fluid Mechanics
  • Rocket Engines

Distribution Statement:

APPROVED FOR PUBLIC RELEASE