AN ANALYTICAL STUDY OF ROTATIONAL FLOW WITH SHOCKS FOR TWO-DIMENSIONAL OR AXISYMMETRIC GEOMETRIES AS APPLIED TO A SPIKE INLET,
Abstract
The Fortran program described in this report is intended for use in computing the inviscid flow field of a hypersonic inlet. (However, separate subroutines for including boundary layer or viscous effects are being dteetermined.) The inlet consists of a curved spike with a blunt tip, followed by an internal contraction section and it can be either two-dimensional or axisymmetric. Curved shocks will stand in front of both the spike tip and the cowl. The effects of entropy gradients (rotational flow) due to such shocks are included in the analysis. The method of construction of shoc reflections from either the inner or outer wall and shock formation due to coalescence of characteristic lines is described. The inlet flow field is divided into two programs. The first program computes the flow field between an input line, the inner wall, the nose shock, and the cowl shock. This program is operational and a programmer's outline is included. At present, slightly supersonic conditions along a line (input line) between the blunt nose and the shock must be provided as inputs to the program. (Author)
Document Details
- Document Type
- Technical Report
- Publication Date
- Oct 10, 1963
- Accession Number
- AD0423532
Entities
People
- A. E. Heins Jr.
- P. J. Aucoin Jr.