Accession Number : ADA302281

Title :   Experimental Investigation of Non-Adiabatic Supersonic Slot Injection into a Supersonic Cross-Flow.

Descriptive Note : Master's thesis,

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

Personal Author(s) : Tucker, Kelly C.

PDF Url : ADA302281

Report Date : 19 DEC 1995

Pagination or Media Count : 155

Abstract : Turbulence and mean flow measurements were acquired downstream of a normal, supersonic (M=1.6), two-dimensional, slot injection into Mach 3.0 flow (Re/m = 15x10 to the 6th power). Two non-adiabatic cases (Tti/Tt = 1.11 and Tti/Tt = 0.93) were studied. Multiple overheat anemometry and conventional mean flow analysis, as well as shadowgraph and schlieren photography, were utilized to study the turbulent mixing layer. The mean flow data included the Pitot, cone-static, and Mach number profiles. The measured turbulence data included shear stresses, mass flux, total temperature turbulence intensities, and turbulent heat fluxes. The temperature and density variation in the flow provided a better understanding of the mixing process. The turbulence mass flux and shear results highlighted the importance of compressibility within the mixing region. The optical analysis showed the physical phenomena of the flow as well as the associated turbulent structure that existed in the mixing layer. (AN)

Descriptors :   *TURBULENCE, *FLOW FIELDS, *SUPERSONIC FLOW, *CROSS FLOW, HEAT TRANSFER, MATHEMATICAL MODELS, INJECTION, DATA MANAGEMENT, THESES, BOUNDARY LAYER, TURBULENT FLOW, COMPUTATIONAL FLUID DYNAMICS, FLOW VISUALIZATION, MASS FLOW, TEMPERATURE GRADIENTS, OPTICAL ANALYSIS, ERROR ANALYSIS, SHEAR STRESSES, DATA ACQUISITION, MACH NUMBER, TWO DIMENSIONAL FLOW, HEAT FLUX, NAVIER STOKES EQUATIONS, VISCOUS FLOW, REYNOLDS NUMBER, ANEMOMETERS, SCHLIEREN PHOTOGRAPHY, SPARK SHADOWGRAPH PHOTOGRAPHY, JET MIXING FLOW.

Subject Categories : Fluid Mechanics

Distribution Statement : APPROVED FOR PUBLIC RELEASE