Accession Number:

AD0654450

Title:

AN APPROXIMATE ANALYSIS OF THE TWO-DIMENSIONAL, SUPERSONIC FLOW PAST A PLANE WALL WITH SUPER-CRITICAL HEAT ADDITION IN A NORMAL PLANE

Descriptive Note:

Technical Report

Corporate Author:

JOHNS HOPKINS UNIV LAUREL MD LAUREL United States

Personal Author(s):

Report Date:

1959-03-01

Pagination or Media Count:

70.0

Abstract:

An analysis is performed to determine approximately the flow field and the normal forces acting for the two-dimensional, supersonic, zero angle-of-attack flow about a flat plate with super-critical heat addition i.e., with thermal choking downstream at a normal finite-height heater plane on one side of the flat plate. The results of the analysis have possible application to the design of an external thrust andor lift producing device for airborne supersonic vehicles. Charts for the determination of the pertinent flow-field parameters and the normal force coefficients as a function of the rate of heat addition and free-stream Mach number, are presented for Mach numbers ranging from 2.0 to 7.0.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE