Accession Number : ADA309553

Title :   Application of Pressure-Sensitive Paint in Shock-Boundary Layer Interaction Experiments.

Descriptive Note : Master's thesis,

Corporate Author : NAVAL POSTGRADUATE SCHOOL MONTEREY CA

Personal Author(s) : Seivwright, Douglas L.

PDF Url : ADA309553

Report Date : MAR 1996

Pagination or Media Count : 202

Abstract : A new type of pressure transducer, pressure-sensitive paint, was used to obtain pressure distributions associated with shock-boundary layer interaction. Based on the principle of photoluminescence and the process of oxygen quenching, pressure-sensitive paint provides a continous mapping of a pressure field over a surface of interest. The data measurement and acquisition system developed for use with the photoluminescence sensor was evaluated first using an underexpanded jet blowing over a flat plate. Once satisfactory results were obtained, the system was used to examine shock-boundary layer interaction in a blow-down supersonic wind tunnel at Mach numbers of 1.4 and 1.7. Details of the measurement technique, and discussion of the flow fields which were examined, are reported.

Descriptors :   *SHOCK WAVES, *BOUNDARY LAYER, *FLOW FIELDS, *PRESSURE DISTRIBUTION, MATHEMATICAL MODELS, SOFTWARE ENGINEERING, IMAGE PROCESSING, DATA MANAGEMENT, OPTICAL DETECTION, PRESSURE TRANSDUCERS, PHOTOLUMINESCENCE, THESES, OPTICAL IMAGES, FLOW VISUALIZATION, PRESSURE MEASUREMENT, DATA REDUCTION, DATA ACQUISITION, PAINTS, MACH NUMBER, INVISCID FLOW, FREE STREAM, VISCOUS FLOW, FLOW SEPARATION, STATIC PRESSURE, JET FLOW, SUPERSONIC WIND TUNNELS, NOZZLE GAS FLOW, IMAGE REGISTRATION, FLAT PLATE MODELS.

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE