Accession Number : AD0855767
Title : Propulsion System Integration and Test Program (Steady State). Part V. Low Speed Auxiliary Inlet Tests.
Descriptive Note : Technical rept. 30 Oct-12 Nov 68 on Phase 2,
Corporate Author : NORTH AMERICAN ROCKWELL CORP LOS ANGELES CA LOS ANGELES DIV
Personal Author(s) : Johnson, Theodore J. ; Huff, Joel H., Jr
Report Date : JUN 1969
Pagination or Media Count : 120
Abstract : A wind tunnel test program was evolved for obtaining experimental performance data on three basic auxiliary inlet configurations incorporated into an inlet typical of the IPS Tactical Fighter inlet. Each of these auxiliary inlet configurations was tested at two axial duct locations and at mach numbers zero, 0.14 and 0.23. The investigation was intended to provide the data necessary to evaluate each auxiliary inlet system and to define the relative performance improvements associated with each. Results from this test program indicate the desirability of using auxiliary inlets for improving inlet performance during take-off and low speed operation. Engine face total pressure recovery and turbulence levels were found to improve with the use of auxiliary inlets although total distortion characteristics were better without auxiliary inlets. (Author)
Descriptors : (*JET FIGHTERS, WING INLETS), (*JET ENGINE INLETS, SUPERSONIC CHARACTERISTICS), AERODYNAMIC CONFIGURATIONS, DUCT INLETS, FLIGHT SPEEDS, PRESSURE, TURBULENCE, AIRCRAFT ENGINES.
Subject Categories : Attack and Fighter Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE