Accession Number : ADA004811

Title :   Investigation of Boundary Layer Shock Interaction at Transonic Speed.

Descriptive Note : Final rept. 1 Jun 72-1 Sep 73,

Corporate Author : NEW YORK UNIV BRONX CENTER FOR INTERDISCIPLINARY PROGRAMS

Personal Author(s) : Panunzio,Sergio

Report Date : JUL 1974

Pagination or Media Count : 63

Abstract : The report describes the design of a facility for studying experimentally the flow field at transonic speed above and near a wing profile, with the objective of determining the supersonic expansion wave-shock configuration. A two-dimensional flow field is considered and a rectangular wing profile, folded into an axially symmetric ring, is used as a model. Test Reynolds numbers are to about 100 million. Modification of the flow field is introduced with (a) variable plenum chamber pressure around the slotted-porous tunnel wall and (b) a mechanism for changing porosity distribution on the slotted wall. Preliminary tests to determine flow uniformity and influence of the variable porosity mechanism are reported.

Descriptors :   *Boundary layer flow, *Transonic characteristics, *Wings, Mathematical prediction, Flow fields, Inviscid flow, Pressure distribution, Walls, Test methods, Experimental design, Shroud rings, Ring wings, Reynolds number, Model tests, Boundary layer control, Shock waves, Transonic wind tunnels

Subject Categories : Aerodynamics
      Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE