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


Personal Author(s) : Moeckel, W E ; Connors, J F ; Schroeder, A H


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/a801322.pdf


Report Date : 17 Jun 1947


Pagination or Media Count : 50


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.


Descriptors :   *DIFFUSERS , *SHOCK MITIGATION , PERFORMANCE(ENGINEERING) , THEORY , SHOCK , CONICAL BODIES , OPTIMIZATION , ANGLES , ANGLE OF ATTACK


Distribution Statement : APPROVED FOR PUBLIC RELEASE