Abstract
A series of perofiles for cascade with the prescribed pressure distributions, which are similar to those of the isolated N.A.C.A. 6409 and 6412 airfoil sections, has been developed. Five blades among the series are tested in the low-speed cascade tunnel with the following conclusions.(i) There exists a fairly good agreement between the theoretical and the experimental turning angles so long as the stagger is not too large.(ii) Two-dimensional losses of a profile in cascade can be reduced to the amount comparable with that of an isolated airfoils by designing a cascade with a favorable pressre distribution.(iii) The discrepancies between the theory and the experiments on pressure rise and pressure distribution over blades are chiefly attributed to the increase in axial velocity through the cascade in the mid-stream.
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