Accession Number : ADA011596
Title : An Experimental Study of Boattail Pressures at High Subsonic Mach Numbers and High Reynolds Numbers.
Descriptive Note : Final rept. 1 Jul 73-30 Jun 74,
Corporate Author : OHIO STATE UNIV RESEARCH FOUNDATION COLUMBUS
Personal Author(s) : Lee,John D.
Report Date : MAR 1975
Pagination or Media Count : 61
Abstract : This study was undertaken to obtain information on the flow over aft-body boattails at high subsonic speeds and at Reynolds numbers representative of the flight range of aircraft. Since the drag of an aircraft is associated with structure surrounding the engine nozzle, the design of that part must depend upon an accurate knowledge of the associated flow field. The covergent shape of the boattail results in a rising pressure, but this produces a thickening and eventual separation of the boundary layer. The effects of the interaction between the viscous and inviscid parts of the flow field form the main objective of this study.
Descriptors : *Aerodynamics, *Boattail afterbodies, *Subsonic characteristics, Flow fields, Aircraft, Aerodynamic drag, Boundary layer flow, Model tests, Flow separation, Pressure distribution, Computer applications, Wind tunnel tests, Data acquisition, Walls, Interference, Interactions, Inviscid flow, Viscous flow
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE