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Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts

Description: Report presenting a new blade series designed to operate at near choking inlet Mach numbers and to have near maximum critical Mach numbers by employing high aerodynamic loading of the profiles in the leading-edge region and relatively straight trailing edges. Results regarding the aerodynamic characteristics and prediction of high-speed performance are provided.
Date: November 26, 1954
Creator: Dunavant, James C.
Partner: UNT Libraries Government Documents Department

Cascade investigation of a related series of 6-percent-thick guide-vane profiles and design charts

Description: Report presenting a description of a new blade series designed to operate at near choking inlet Mach numbers and to have near maximum critical Mach numbers by employing high aerodynamic loading of the profiles in the leading-edge region. Results regarding aerodynamic characteristics and prediction of high-speed performance are provided.
Date: May 1957
Creator: Dunavant, James C.
Partner: UNT Libraries Government Documents Department

A compressible-flow plotting device and its application to cascade flows

Description: Report presenting a simplified method for the solution of two-dimensional compressible flows through well-defined passages. Pressure distributions around four cascades of turbine blades and along the surface of a choked nozzle determined by the method are shown to compare well with experimental results.
Date: April 1952
Creator: Wesphal, Willard R. & Dunavant, James C.
Partner: UNT Libraries Government Documents Department

Two-dimensional cascade investigation at Mach numbers up to 1.0 of NACA 65-series blade sections at conditions typical of compressor tips

Description: Report presenting a two-dimensional high-speed cascade investigation of thin low-cambered NACA 65-series blade shapes at operating conditions typical of compressor tip sections. Testing occurred with porous walls and solid walls. Results regarding the variation of turning angle with Mach number, variation of turning angle with angle of attack, momentum loss, and schileren photographs are provided.
Date: March 17, 1958
Creator: Dunavant, James C. & Emery, James C.
Partner: UNT Libraries Government Documents Department

Investigation of a related series of turbine-blade profiles in cascade

Description: Report presenting an application of airfoil design methods to a series of related turbine-blade profiles to satisfy the conditions of inlet flow angle and turning angle encountered in the usual range of turbine operation. Satisfactory flow conditions were obtained in all of the blade passages tested. Results regarding the turning angles, wake losses, surface pressure distributions, critical Mach numbers, application of compressibility corrections to low-speed tests, and selection of design camber are provided.
Date: October 1956
Creator: Dunavant, James C. & Erwin, John R.
Partner: UNT Libraries Government Documents Department

Investigation of a Related Series of Turbine-Blade Profiles in Cascade

Description: From Summary: "An application of airfoil design methods was used to design series of related turbine-blade profiles to satisfy the conditions of inlet flow angle and turning angle encountered in the usual range of turbine operation. A series of blade profiles applicable to most turbine blading requirements and a secondary series with particular reference to impulse conditions were designed. Five blade sections from these series ranging in mean-line turning angles from 63 deg. to 120 deg. were tested in low-speed cascade tunnels."
Date: December 7, 1953
Creator: Dunavant, James C. & Erwin, John R.
Partner: UNT Libraries Government Documents Department

Application of the wire-mesh plotting device to incompressible cascade flows

Description: From Summary: "The methods used in the application of the wire-mesh plotting device to find the flow pattern about a cascade of airfoils in compressible inviscid flow and some mathematical checks that increase the accuracy of this application are described. Results for two typical turbine-blade cascades are shown to compare well with experimental data. A method of utilizing the wire mesh to design turbine blades with a prescribed pressure distribution in incompressible flow is presented."
Date: May 1950
Creator: Westphal, Willard R. & Dunavant, James C.
Partner: UNT Libraries Government Documents Department

Two-dimensional cascade tests of NACA 65-(C(sub zeta)(sub o))A(sub 10))10 blade sections at typical compressor hub conditions for speeds up to choking

Description: Report presenting two-dimensional porous-wall cascade tests of specified NACA blade sections at typical compressor hub conditions at speeds up to choking. For typical compressor blade hub sections, the angle of attack for best operation at high Mach numbers is about 6 degrees higher than the design angle of attack for low speeds. Results regarding the 65-series blade tests and circular-arc blade-section tests are provided.
Date: October 23, 1957
Creator: Emery, James C. & Dunavant, James C.
Partner: UNT Libraries Government Documents Department

High-Speed Cascade Tests of the NACA 65-(12A(sub 10))10 and NACA 65-(12A(sub 2)I(sub 8b))10 Compressor Blade Sections

Description: From Summary: "Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade sections were made at Mach numbers from 0.3 to choking in most cases. Data were obtained at solidities of 1.0 and 1.5 at inlet-air angles of 45 deg. and 60 deg. for both blade sections. With a solid--wall modification to the cascade tunnel, schlieren observations were made of the flow in cascade at a solidity of 1.5 and inlet-air angle of 45 deg. and at a solidity of 1.0 and inlet-air angle of 60 deg."
Date: December 21, 1955
Creator: Dunavant, James C.; Emery, James C.; Walch, Howard C. & Westphal, Willard R.
Partner: UNT Libraries Government Documents Department