Accession Number : AD0858916
Title : Propulsion System Integration and Test Program (Steady State). Part IV. Inlet Drag Tests.
Descriptive Note : Technical rept. 26 Jul-12 Aug 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 : 248
Abstract : A wind tunnel test program was evolved for obtaining experimental performance data on a mach 2.5, two-dimensional, external compression inlet typical of the IPS Tactical Fighter inlet. Tests were conducted at mach numbers of 0.6, 0.85, 0.95, 1.2, 1.3, 1.7 and 2.2. The investigation was intended to provide the data necessary to evaluate installation effects and to substantiate analytic methods of performance predictions. (Author)
Descriptors : *JET FIGHTERS, *JET ENGINE INLETS, DRAG, SUPERSONIC CHARACTERISTICS, TWO DIMENSIONAL FLOW, PERFORMANCE(ENGINEERING), WIND TUNNEL MODELS, MODEL TESTS.
Subject Categories : Aerodynamics
Attack and Fighter Aircraft
Jet and Gas Turbine Engines
Distribution Statement : APPROVED FOR PUBLIC RELEASE