Accession Number:

ADA289477

Title:

Compressible Turbulence Measurements in a Supersonic Flow With Adverse Pressure Gradient.

Descriptive Note:

Master's thesis,

Corporate Author:

AIR FORCE INST OF TECH WRIGHT-PATTERSON AFB OH SCHOOL OF ENGINEERING

Personal Author(s):

• Dotter, Jon W.

Report Date:

1994-12-01

Pagination or Media Count:

121.0

Abstract:

Mean flow and compressible turbulence measurements have been obtained upstream and within a shock boundary interaction and a compression ramp in Mach 3 flow. Compressible turbulence models have met with little success in the accurate prediction of high-speed flows involving complicated shock boundary interactions and adverse pressure gradients because of a crucial lack of experimental data. Data were collected using conventional Pitot and cone static probes, single overheat cross-wire anemometry, multiple overheat cross-wire anemometry, and flow visualization techniques. Direct measurements of the total Reynolds shear stress were obtained using a turbulence transformation. Results indicate that compressibility effects, as evidenced by the density fluctuations, are large relative to the velocity fluctuations and should be accounted for rigorously in new turbulence models.

Descriptors:

• *PRESSURE GRADIENTS
• *TURBULENT FLOW
• *PRESSURE MEASUREMENT
• *SUPERSONIC FLOW
• COMPRESSION
• STRESSES
• VELOCITY
• DENSITY
• EXPERIMENTAL DATA
• PREDICTIONS
• TIME DEPENDENCE
• MODELS
• INTERACTIONS
• HIGH VELOCITY
• ACCURACY
• THESES
• FLOW VISUALIZATION
• VARIATIONS
• BOUNDARIES
• SHOCK
• SHEAR STRESSES
• DATA REDUCTION
• ADVERSE CONDITIONS
• INSTRUMENTATION
• MEAN
• NAVIER STOKES EQUATIONS
• RAMPS
• TRANSFORMATIONS
• COMPRESSIVE PROPERTIES
• MOMENTUM TRANSFER
• HOT WIRE

Subject Categories:

• Fluid Mechanics

Distribution Statement:

APPROVED FOR PUBLIC RELEASE