Accession Number : ADA329733
Title : Laminar-Turbulent Transition in High-Speed Compressible Boundary Layers with Curvature: Non-Zero Angle of Attack Experiments
Descriptive Note : Final rept. 1 Jul 94-30 Jun 97
Corporate Author : PURDUE UNIV LAFAYETTE IN
Personal Author(s) : SCHNEIDER, Steven P. ; Collicott, Steven H.
PDF Url : ADA329733
Report Date : 15 AUG 1997
Pagination or Media Count : 7
Abstract : This grant supported the work of two additional graduate students in the area of high speed boundary layer transition. The non-zero angle of attack measurements were delayed, to reduce the risk of damaging the model, currently in use at zero angle of attack (AOA). Instead, a high sensitivity laser differential interferometer is being developed, for non-intrusive high bandwidth measurements of instability waves. Work towards the larger wind tunnel discussed in the proposal was also advanced, through measurements of the effect of elevated driver tube temperatures on the extent of quiet flow. Apparatus for placement of the elliptic cone at a 3-degree AOA has been designed; these measurements will commence on completion of the zero AOA measurements, late in 1997.
Descriptors : *ANGLE OF ATTACK, *BOUNDARY LAYER TRANSITION, *SUPERSONIC WIND TUNNELS, TURBULENT FLOW, TURBULENT BOUNDARY LAYER, INTERFEROMETRY, COMPRESSIBLE FLOW, FLOW FIELDS, WIND TUNNEL TESTS, MACH NUMBER, SUPERSONIC FLOW, LAMINAR FLOW, LAMINAR BOUNDARY LAYER.
Subject Categories : Aerodynamics
Distribution Statement : APPROVED FOR PUBLIC RELEASE