Accession Number : AD0866553
Title : Propulsion System Flow Stability Program (Dynamic). Part VI. Inlet Turbulence Scaling.
Descriptive Note : Final technical rept. 1 Oct 68-1 Dec 69 on Phase 2,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV
Personal Author(s) : Beaulieu, Warren D. ; Boyd, Harry E., Jr. ; Kostin, Leonard C. ; Martin, Arnold W.
Report Date : FEB 1970
Pagination or Media Count : 327
Abstract : During the development phase of an aircraft propulsion system, the inlet-induced turbulence to which the engine will be subjected must be projected from model test data. A test program has been conducted to investigate the effects of inlet scale on turbulence and to determine methods for correcting model data to full-scale conditions. Geometrically similar 0.30- and 0.125-scale inlet/forebody models and a modification of the 0.125-scale model were tested with the objectives of separating the effects of scale, Reynolds number and length on inlet-induced turbulence. Statistical parameters, steady-state and instantaneous pressure patterns, and time histories of various pressure parameters were used in the data analysis. To provide guidance to the data analysis, a conceptual model of the turbulence generation and decay process was hypothesized. (Author)
Descriptors : (*RECONNAISSANCE AIRCRAFT, TURBOJET ENGINES), (*TURBOJET ENGINES, AXIAL FLOW COMPRESSORS), (*AXIAL FLOW COMPRESSORS, FLOW SEPARATION), STABILITY, TURBULENCE, TURBULENT BOUNDARY LAYER, REYNOLDS NUMBER, STATISTICAL ANALYSIS, PROBABILITY, ANGLE OF ATTACK, WIND TUNNEL MODELS, MATHEMATICAL MODELS, TACTICAL AIR SUPPORT, ADVANCED WEAPONS.
Subject Categories : Aerodynamics
Patrol and Reconnaissance Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE