Application of theoretical design methods to the study of performance limits of airfoils in cascade.
Jenista, John E.
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A method of designing airfoils in cascade by means of conformal transformations is discussed. Design of these airfoils is regulated by five independent input parameters, with solutions obtained by digital computer., A large number of cascades generated by this method are compared. To evaluate the limits of performance, a parameter to indicate the tendency toward flow separation is introduced, with a limiting value established and verified. Proper solidity is shown to be of great importance in achieving low values of this separation parameter. The value of proper solidity for a given blade thickness is shown to be relatively independent of fairing shape. To increase performance, reducing blade thickness with a corresponding increase in solidity is shown to yield much greater improvement than changes in fairing shape.
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Cina, Frank S. (1981);Tests are reported in which air incidence angle was varied to a cascade of 20 blades, 5 inches in chord with aspect ratio of 2.0 and solidity of 1.67. Preliminary blade element performance data were obtained using ...
Chalkley, Henry George (1972-06);Supersonic flow past oscillating flat plate cascades with supersonic leading-edge locus is analysed using a linearized method of characteristics valid for arbitrary frequencies and an elementary analytical theory valid ...
Koyuncu, Yuksel (Monterey, California. Naval Postgraduate School, 1984-03);Results of 14 tests in a subsonic cascade are reported in which the air inlet angle and Reynolds number were varied. The cascade contained 20 Controlled Diffusion (CD) blades , with 5.01 inches chord, aspect ratio of 2.0 ...