Accession Number:

AD0645981

Title:

ANALYTICAL AND EXPERIMENTAL INVESTIGATION OF SUPERSONIC INJECTORS WITH LARGE SECONDARY MASS FLOWS,

Descriptive Note:

Corporate Author:

AEROSPACE RESEARCH LABS OFFICE OF AEROSPACE RESEARCH WRIGHT-PATTERSON AFB OHIO

Personal Author(s):

Report Date:

1966-08-01

Pagination or Media Count:

57.0

Abstract:

A series of experimental tests were performed with airair constant area supersonic injectors, and typical results are presented here. Data were taken with secondary mass flows, both larger and smaller in magnitude than the primary mass flow. One of the constant area injectors produced a remarkable pumping efficiency of 30 with equal mass flows in the primary and secondary. A special constant area mixing tube was constructed and tested. This test indicated a ratio 5LD8 for completion of the shock-mixing process in a straight tube. Calculations are given for an analytical model of an injector consisting of a constant pressure mixing section followed by a constant area section containing an effective, normal shock pattern. Both airair and mercuryhelium injectors were treated in the calculations. The geometry of the constant pressure-normal shock injector was found to differ only slightly from a constant area injector. Experimental tests of constant pressure-normal shock injectors resulted in performances considerably below the theoretical calculations and nearly identical to the experimental data taken with the constant area injectors. Author

Subject Categories:

  • Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE