Accession Number : AD0875187
Title : A Problem in Matching an Inlet and Engine Having Steady-State Circumferential Inlet Pressure Distortion,
Corporate Author : NAVAL AIR PROPULSION TEST CENTER TRENTON NJ AERONAUTICAL TURBINE DEPT
Personal Author(s) : Brunda, Donald F.
Report Date : AUG 1970
Pagination or Media Count : 16
Abstract : An analysis was made of the flow redistribution which occurs at the exit of an inlet due to the presence of a compressor. The flow redistribution includes a change in the axial velocity distortion, which is a function of the slope of the curve of compressor pressure coefficient versus flow coefficient at a particular corrected speed. (Author)
Descriptors : *ENGINE AIR SYSTEMS COMPONENTS), (*AIRCRAFT ENGINES, DISTORTION, PRESSURE, DISTRIBUTION, GAS FLOW, COMPRESSORS.
Subject Categories : Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE