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
Descriptors:
- *NOZZLE GAS FLOW
- *AXISYMMETRIC FLOW
- COMPUTATIONS
- FINITE DIFFERENCE THEORY
- FLOW FIELDS
- BOUNDARY VALUE PROBLEMS
- NUMERICAL METHODS AND PROCEDURES
- NAVIER STOKES EQUATIONS
- VISCOUS FLOW
- LAMINAR FLOW
- THRUST VECTOR CONTROL SYSTEMS
- REYNOLDS NUMBER
- HYPERSONIC WIND TUNNELS
- BOUNDARY LAYER FLOW
- CHEMICAL LASERS
- UNITED KINGDOM
Subject Categories:
- Fluid Mechanics