Download or read book Analysis of Aerodynamic Blade loading limit Parameters for NACA 65 C sub Zeta 0A10 10 Compressor blade Sections at Low Speeds written by Melvyn Savage and published by . This book was released on 1955 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Analysis of Aerodynamic Blade loading limit Parameters for NACA 65 C iota O A 10 10 Compressor blade Sections at Low Speeds written by Melvyn Savage and published by . This book was released on 1955 with total page 32 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book High Speed Cascade Tests of the Naca 65 10 and Naca 65 I 10 Compressor Blade Sections written by James C. Dunavant and published by BiblioGov. This book was released on 2013-07 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 et 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. Test results for the NACA 65-(12A10)l0 blade section show t hat the turning angles measured at low speed do not change significantly as the speed increases until the critical Mach number is exceed. Because of increasing separation from the highly cambered trailing-edge region, the turning angles for the NACA 65-(12A2I8b)10 blade section decreased as much as 4 deg. from low speed to critical speed. The high-speed performance of the NACA 65-(12A10)10 and the NACA 65-(12A2I8b)l0 blade sections is largely determined by the passage area distribution. The angle of attack for best operation at high Mach numbers is higher than the design angle of attack selected at low speed to have pressure distributions that are free of peaks.
Download or read book Two dimensional Low speed Cascade Investigation of NACA Compressor Blade Sections Having a Systematic Variation in Mean line Loading written by John R. Erwin and published by . This book was released on 1953 with total page 136 pages. Available in PDF, EPUB and Kindle. Book excerpt: Comparative tests of blade sections having an isolated airfoil lift coefficient of 1.2 were made for two other blade sections with mean lines having different loading distributions at an inlet angle of 45 degrees with a solidity of 1.5 and at an inlet angle of 60 degrees with a solidity of 1.0.
Download or read book Two dimensional Cascade Tests of NACA 65 Lift Coefficient 0 A 10 10 Blade Sections at Typical Compressor Hub Conditions for Speeds Up to Choking written by James C. Emery and published by . This book was released on 1957 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Low speed Cascade Investigation of Thin Low camber NACA 65 series Blade Sections at High Inlet Angles written by James C. Emery and published by . This book was released on 1957 with total page 93 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Procedure for Calculating Turbine Blade Temperatures and Comparison of Calculated with Observed Values for Two Stationary Air cooled Blades written by W. Byron Brown and published by . This book was released on 1952 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: Local and average blade temperatures were calculated for two stationary air-cooled turbine blades with 10 tubes and 13 fins forming the internal heat-transfer surfaces. These temperatures were calculated using previously published NACA temperature-distribution equations and the most recent theories for determining heat-transfer coefficients, including for the first time the allowance for effects of variable wall temperature on gas-to-blade heat-transfer coefficients at the leading and trailing sections of turbine blades. Comparison of calculated and experimental blade temperatures, for gas temperatures of 300° and 1000°F, resulted in good agreement.
Download or read book Two dimensional Cascade Investigation at Mach Numbers Up to 1 0 of NACA 65 series Blade Sections at Conditions Typical of Compressor Tips written by James C. Dunavant and published by . This book was released on 1958 with total page 185 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Diffusion Factor for Estamating Losses and Limiting Blade Loadings in Axial flow compressor Blade Elements written by Seymour Lieblein and published by . This book was released on 1953 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Aerodynamic Characteristics at High Speeds of a Two blade NACA 10 3 062 045 Propeller and of a Two blade NACA 10 3 08 45 Propeller written by William Solomon and published by . This book was released on 1948 with total page 54 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book Cascade Investigation of a Related Series of 6 percent thick Guide vane Profiles and Design Charts written by James C. Dunavant and published by . This book was released on 1957 with total page 47 pages. Available in PDF, EPUB and Kindle. Book excerpt: 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 training edges is described. Low-speed cascade tests of four blade sections at solidities of 0.75, 1.00, and 1.50 were made over a wide range of angle of attack. From these tests, design angles of attack were selected and were used in a method of determining the camber for guide -vane turning angles as high as 50 degrees. All turning angles measured at low drag conditions are plotted by the carpet-plotting method and from interpolation the necessary camber is readily obtainable for conditions other than those tested. A number of simple computations were made to estimate the high-speed characteristics of the blade series.
