Accession Number:

AD0851947

Title:

An Experimental Study of the Effect of Inlet Geometry on Flow and Performance of a Supersonic Nozzle

Descriptive Note:

Master's thesis

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

Report Date:

1969-03-01

Pagination or Media Count:

67.0

Abstract:

This study is an experimental evaluation of the performance of 12 two-dimensional, converging-diverging, cold flow, supersonic nozzles, each with the same throat and divergent section. The relative efficiency of each nozzle was evaluated by a comparison of total pressure measurements taken in the exit plane, schlieren photographs of the flow, and heat transfer characteristics using moire patterns. The nozzle with the highest efficiency had an inlet which was an ellipse faired to a 45 degree ramp. Its performance was closely followed by that of a nozzle with a circular arc inlet having a radius of three times the throat height. The three nozzles with the lowest efficiencies were those with 30, 45, and 60 degrees linear ramp inlets, respectively. The results of this study indicate that, in nozzle design, a region of immense importance is the curvature just prior to the throat and how this curvature is joined to the throat section.

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE