Accession Number : AD0510537
Title : Large Scale Inlet Distortion Investigation.
Descriptive Note : Technical rept. 20 Sep 68-30 Apr 69,
Corporate Author : GENERAL ELECTRIC CO CINCINNATI OH
Personal Author(s) : Kutschenreuter, P. H., Jr. ; Burnett, G. A. ; Moore, M. T.
Report Date : MAY 1970
Pagination or Media Count : 163
Abstract : The objectives of this program were to provide an early assessment of inlet performance and distortion characteristics at critical inlet/engine operating points for an inlet design installation representative of advanced tactical aircraft. A fuselage installed, two dimensional, horizontal ramp, external compression, variable geometry, large scale inlet model was tested at both subsonic and supersonic speeds from M = 0.6 to M = 2.2. Inlet recovery, steady-state and dynamic distortion characteristics were experimentally determined over a wide range of angle of attack and yaw from alpha = -5 deg to 20 deg and beta = -10 deg to +10 deg. Constant band width FM multiplexing was used to obtain time phased fluctuating pressure characteristics at the inlet/engine interface. Recently developed computational techniques were used to process selected dynamic distortion data for use in the design of advanced engines for tactical aircraft. (Author)
Descriptors : (*JET ENGINE INLETS, DISTORTION), AERODYNAMIC CONFIGURATIONS, INTERFACES, TACTICAL WEAPONS, MODEL TESTS, MODELS(SIMULATIONS), PRESSURE, RECOVERY, DUCT INLETS, BOUNDARY LAYER, YAW, DEFECTS(MATERIALS), ADVANCED WEAPONS (U) RECONNAISSANCE AIRCRAFT, JET BOMBERS, ATTACK BOMBERS, NAVAL AIRCRAFT, TRANSONIC CHARACTERISTICS, SUPERSONIC CHARACTERISTICS, ANGLE OF ATTACK, SUPERSONIC DIFFUSERS, FREQUENCY MODULATION, MULTIPLEXING.
Subject Categories : Fluid Mechanics
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE