Accession Number:

ADA801322

Title:

Investigation of Shock Diffusers at Mach Number 1.85. 1 - Projecting Single Shock Cones

Descriptive Note:

Research memo.

Corporate Author:

NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS CLEVELAND OH LEWIS FLIGHT PROPULSION LAB

Report Date:

1947-06-17

Pagination or Media Count:

50.0

Abstract:

Design conditions for optimum performance of shock diffusers are determined. Single-shock cones used had angles varying from 20 to 70 deg Fahrenheit. Each cone was tested with curved and straight diffusers-inlet sections. Effect of angle of attack was investigated for several configurations. Maximum total-pressure recovery was obtained with 50 deg Fahrenheit cone using straight inlet. Highest total-pressure recoveries were attained with subsonic entrance flow. Variation of maximum total-pressure recovery with cone angle concurred with theoretical analyses.

Subject Categories:

Distribution Statement:

APPROVED FOR PUBLIC RELEASE