Accession Number : AD0646397
Title : SPLITTER EFFECT IN CONICAL DIFFUSERS. PART III. COMPRESSIBILITY EFFECT. PART IV. PRESSURE DISTRIBUTION.
Descriptive Note : Technical rept.,
Corporate Author : CLEMSON UNIV S C ENGINEERING EXPERIMENT STATION
Personal Author(s) : Yang,Tah-teh ; Kirkwood,Charles E. ; Jones,Hal O.
Report Date : NOV 1966
Pagination or Media Count : 68
Abstract : An investigation was made concerning the effect of inlet velocity on the pressure recovery efficiency of a subsonic conical diffuser with and without a ring-airfoil installed. Three diffusers and two ring-airfoils were tested over a range of inlet Mach Number 0.30< or = M< or = 0.70. The conclusions reached for diffusers with and without ring-airfoils are: (1) the compressibility (Mach Number) effect is small compared to the Scaling (Reynolds Number) effect, (2) there is an optimum Mach Number for each diffuser at which the pressure recovery efficiency is a maximum, and (3) pressure recovery efficiency variation with respect to Mach Number ranged from 3 to 7% over the range .25< or = M< or = .70. Experimental results are presented for conical diffusers with and without a ring-airfoil mounted. (Author)
Descriptors : (*DIFFUSERS, CONICAL BODIES), AIRFOILS, PRESSURE, EFFICIENCY, COMPRESSIVE PROPERTIES, RINGS, SUBSONIC FLOW, MACH NUMBER
Subject Categories : Fluid Mechanics
Distribution Statement : APPROVED FOR PUBLIC RELEASE