R. F. Cuffel

Effect of Mild Atherosclerosis on Flow Resistance in a Coronary Artery Casting of Man

An in-vitro flow study was conducted in a mildly atherosclerotic main coronary artery casting of man using sugar-water solutions simulating blood viscosity. Steady flow results indicated substantial increases in pressure drop, and thus flow resistance at the same Reynolds number, above those for Poiseuille flow by 30 to 100 percent in the physiological Reynolds number range from about 100 to 400. Time-averaged pulsatile flow data showed additional 5 percent increases in flow resistance above the steady flow results. Both pulsatile and steady flow data from the casting were found to be nearly equal to those from a straight, axisymmetric model of the casting up to a Reynolds number of about 200, above which the flow resistance of the casting became gradually larger than the corresponding values from the axisymmetric model.

Flow phenomena and convective heat transfer in a conical supersonic nozzle.

Turbulent boundary layer flow in conical supersonic nozzle, discussing convective heat transfer and adverse pressure gradient effect

Laminarization of a Turbulent Boundary Layer in Nozzle Flow—Boundary Layer and Heat Transfer Measurements With Wall Cooling

Boundary layer and heat transfer measurements for turbulent boundary layer laminarizing in conical nozzle flow with wall cooling

Some observations on reduction of turbulent boundary-layer heat transfer in nozzles.

Convective heat transfer in accelerated heated air flows through cooled conical supersonic nozzles of three different configurations

Influence of contraction section shape and inlet flow direction on supersonic nozzle flow and performance.

Wall static pressure measurements and performance parameters are presented for axisymmetric supersonic nozzles with relatively steep convergent sections and comparatively small radius-of-curvature throats. The nozzle walls were essentially adiabatic. These results are compared with those obtained in other nozzles tested previously to appraise the influence of contraction shape on performance. Both the flow coefficient and the thrust were less than the corresponding values for one-dimensional, isentropic, plane flow for both the axial and radial inflow nozzles considered, but the specific impulse, the most important performance parameter, was found to be relatively unchanged. The thrust decrement for the axial inflow nozzles was established primarily by the shape of the contraction section, and could be estimated reasonably well from a conical sink flow consideration. The radial inflow nozzle has a potential advantage from a cooling point of view if used in a rocket engine.

Heat-transfer measurements in the shock-induced flow separation region in a supersonic nozzle.

Pressure and semilocal wall heat flux measurements in shock induced flow separation region in supersonic nozzle, noting shock waves-flow interaction

Laminar, Transition, and Turbulent Boundary-Layer Heat-Transfer Measurements With Wall Cooling in Turbulent Airflow Through a Tube

Laminar, transition and turbulent boundary layer heat transfer measurements along wall in thermal entrance region of high temperature turbulent airflow through cooled tube

Flow and heat transfer measurements along a cooled supersonic diffuser

An experimental investigtion was conducted to ascertain the mean flowfield, including shock wave structure, separated flow regions, turbulent boundary-layer growth, static pressure variations, wall heat transfer, and shear stresses in a second-throat, axisymmetric, supersonic diffuser with wall cooling. The diffuser inlet Mach number of the heated air flow was 3.76, the stagnation pressure was 6.8 atm, the ratio of wall to total gas temperature was 0.44, and the diffuser discharged to the atmosphere. The complex flowfield involved deceleration and acceleration regions, supersonic and embedded subsonic regions, and strong viscous regions with relatively large radial and axial variations. The heat transfer and wall static pressure distributions were remarkably similar, and heat transfer rates were high locally at oblique shock/turbulent boundary-layer interactions, in the pseudoshock region, and in the separation region in the diffuser outlet section.