Accession Number:

ADA058411

Title:

An Implicit Finite Difference Procedure for the Laminar, Supersonic Base Flow.

Descriptive Note:

Doctoral thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1978-01-01

Pagination or Media Count:

136.0

Abstract:

The development of a tool for solving the near field of a scramjet fuel injector was attacked by first developing a numerical technique for solving the laminar, supersonic near wake flow. It was considered important to develop a procedure that had a potential for reduced computation time compared with explicit methods. The implicit numerical procedure was extended to mixed subsonicsupersonic flow with shocks, expansions, and regions of reverse flow. In the present case, numerical results have been obtained for the laminar, supersonic near wake behind a rectangular base. This numerical method produced stable, convergent, and accurate solutions when applied to this complex flow problem.

Subject Categories:

  • Fluid Mechanics
  • Combustion and Ignition

Distribution Statement:

APPROVED FOR PUBLIC RELEASE