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Boundary layer effects on airfoil lift
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
A study of the discrepancy in lift between potential flow calculations and experiments was made. In potential flow the fluid is assumed to follow the contour of the airfoil, forming a stagnation point at the geometric ...
Boundary layer on an airfoil in a cascade
([Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
A study of the turbulent boundary layer on an airfoil in a cascade is presented. The major portion of the observations are on the suction surface of the airfoil. The effect of added diffusion across the cascade due to a ...
The three-dimensional turbulent boundary layer in a free vortex diffuser
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
Experimental velocity profiles and static pressure measurements were obtained from the flow in a free vortex diffuser. The purpose of the study was to obtain additional three dimensional boundary layer data and to compare ...
The design of axial inducers for turbo-pumps
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
In many turbopump applications it is desirable to run the pump at the highest possible speed to minimise the size and weight of the unit and facilitate matching with a drive turbine. Frequently, a limit on rotational speed ...
Secondary flow and losses in a compressor cascade
(Cambridge, Mass. : Gas Turbine Laboratory, Massachusetts Institute of Technology, [1958], 1958)
Three ways in which secondary flow can be generated in a straight compressor cascade have been investigated. 1. Wakeflow. The inlet flow is characterized by a constant inlet angle and a varying stagnation pressure over the ...