Application of theoretical design methods to the study of performance limits of airfoils in cascade.
Jenista, John E.
MetadataShow full item record
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.
RightsThis publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.
Showing items related by title, author, creator and subject.
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 ...