Accession Number:

AD0274329

Title:

EFFECTS OF SUCTION BOUNDARY-LAYER CONTROL ON THE PERFORMANCE OF A SHORT ANNULAR DIFFUSER WITH AN UPSTREAM TERMINAL NORMAL SHOCK

Descriptive Note:

Corporate Author:

NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON DC

Report Date:

1962-04-01

Pagination or Media Count:

64.0

Abstract:

A normal shock was positioned at distances ranging from 0.4 to 2.0 annulus gaps upstream from the diffuser entrance the corresponding shock Mach number ranged from 1.40 to 1.47. Boundary layer suction flows as high as about 13 percent of the diffuser entrance flow were employed. The equivalent conical expansion angle of the diffuser was 10 degrees with about 5-percent suction flow, the over-all total pressure loss of the 10 degrees diffuser was less than that for a 5 degrees diffuser with no boundary-layer control. Pumping-power considerations indicated that suction-flow rates from 5 to 8 percent were economical relative to improved diffuser performance.

Subject Categories:

  • Machinery and Tools

Distribution Statement:

APPROVED FOR PUBLIC RELEASE