Accession Number:

ADA055124

Title:

Laminar Flow-Field Computation in Axisymmetric Nozzles.

Descriptive Note:

Technical rept.,

Corporate Author:

ROYAL AIRCRAFT ESTABLISHMENT FARNBOROUGH (ENGLAND)

Personal Author(s):

Report Date:

1977-11-01

Pagination or Media Count:

35.0

Abstract:

A numerical procedure for computing the laminar flow-field in nozzles at throat Reynolds numbers of 300-3000 is described. Such nozzles are found in spacecraft position control thrusters, chemical lasers, and low density hypersonic wind-tunnels. A parabolic approximation of the Navier-Stokes equations the boundary layer equations is transformed to Von Mises form and solved numerically by a central difference method. The entire subsonic and supersonic flow-field is computed. No assumptions or approximations, other than those inherent in the flow equations, are involved. The method is of the direct type and the flow-field for any given nozzle geometry may, in principle, be computed. Examples are given comparing computed results with published experimental data. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE