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Analysis Of Aerodynamic Blade Loading Limit Parameters For Naca 65 C Sub Zeta 0a10 10 Compressor Blade Sections At Low Speeds Book in PDF, ePub and Kindle version is available to download in english. Read online anytime anywhere directly from your device. Click on the download button below to get a free pdf file of Analysis Of Aerodynamic Blade Loading Limit Parameters For Naca 65 C Sub Zeta 0a10 10 Compressor Blade Sections At Low Speeds book. This book definitely worth reading, it is an incredibly well-written.
Author : Melvyn Savage
Publisher : Unknown
Page : 38 pages
File Size : 45,7 Mb
Release : 1955
Category : Axial flow compressors
ISBN : UOM:39015086465740
Author : Willard R. Westphal
Publisher : Unknown
Page : 60 pages
File Size : 41,5 Mb
Release : 1951
Category : Aerodynamic load
ISBN : UOM:39015086464784
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure distribution obtained in the compressor at design conditions. At other than design angle of attack, large differences, probably due to secondary flows, were observed near the inner casing.
Author : Anonim
Publisher : Unknown
Page : 102 pages
File Size : 54,8 Mb
Release : 19??
Category : Aerodynamics
ISBN : STANFORD:36105024809647
Author : J. J. Moses,G. K. Serovy
Publisher : Unknown
Page : 18 pages
File Size : 42,9 Mb
Release : 1951
Category : Aeronautics
ISBN : UOM:39015086431965
Author : John R. Erwin,Melvyn Savage,James C. Emery
Publisher : Unknown
Page : 136 pages
File Size : 43,9 Mb
Release : 1953
Category : Aerofoils
ISBN : UOM:39015086465450
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.
Author : James C. Emery
Publisher : Unknown
Page : 84 pages
File Size : 55,5 Mb
Release : 1956
Category : Cascades (Fluid dynamics)
ISBN : UOM:39015086465955
Author : Charles M. Zimmey,Viola M. Lappi
Publisher : Unknown
Page : 62 pages
File Size : 49,5 Mb
Release : 1945
Category : Aerodynamics
ISBN : UFL:31262081065095
Data obtained from tests of five NACA blower-blade sections and four experimentally driven sections are presented in the form of entrance vane design charts for axial-flow compressors or turbines. These charts give blade section and angle of attack for any turning angle. Blades thus obtained operate with peak-free pressure distributions. These series of blower-blade sections, with relatively high critical speeds, will efficiently turn air flowing in an axial direction from 0 to 80 degrees.
Author : E. O. Pearson,A. J. Evans,F. E. West
Publisher : Unknown
Page : 48 pages
File Size : 40,8 Mb
Release : 1945
Category : Aerodynamic load
ISBN : UFL:31262081049735
Force and pressure-distribution measurements were made on a fighter-type wing model of conventional NACA 230-series airfoil sections in the Langley 16-foot high-speed tunnel to determine the effects of compressibility on the maximum lift characteristics and the span-wise load distribution. The range of angle of attack investigated was from -10 to +24 degrees. The Mach range of from 0.20 to 0.70 at small and medium angles of attack and from 0.15 to 0.625 at very large angles of attack. Maximum lift coefficient increased up to a Mach number of 0.3, decreased rapidly to a Mach number of 0.55, and then decreased moderately. At high speeds, maximum lift coefficient was reached at from 10 to 12 degrees beyond the stalling angle. In high-speed stalls, resultant load underwent a moderate shift outward.
Author : John R. Erwin,Melvyn Savage,James C. Emery
Publisher : Unknown
Page : 129 pages
File Size : 51,9 Mb
Release : 1956
Category : Compressors
ISBN : OCLC:249877449
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.
Author : George G. Edwards
Publisher : Unknown
Page : 658 pages
File Size : 45,8 Mb
Release : 1956
Category : Aerodynamics
ISBN : STANFORD:36105024832177
An investigation has been conducted at speeds up to a Mach number of 0.90 to determine the effects of operating propellers on the longitudinal characteristics of a four-engine tractor airplane configuration having a 40 degrees swept wing with an aspect ratio of 10. Results of wind-tunnel tests of a model representing such an airplane configuration (see NACA TN 3789) show that these effects are of most concern in the low-speed high-thrust flight regime. In the present report the low-speed data are analyzed to determine the source of the various effects and to indicate how the adverse effects can be reduced, and the high-speed data are discussed primarily from the standpoint of Mach number effects. The analysis of the low-speed data indicates that the large variations of longitudinal stabil.itywith angle of attack resulted primarily from passage of the tail into and out of the slipstream. The slipstream also created large lift increments on the wing, particularly with flaps deflected, which resulted in increases in stability (with increasing thrust coefficient) from the outboard propeller and decreases in stability from the inboard propeller. It was concluded that the longitudinal stabiltty characteristics of the model couldbe improved by moving the nacelles outward, increasing the tail height, and reducing the tail span.
Author : Jack F. Runckel
Publisher : Unknown
Page : 104 pages
File Size : 40,6 Mb
Release : 1956
Category : Aerodynamic load
ISBN : UOM:39015095100999
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections has been conducted in the Langley16-foot transonic tunnel. Pressure measurements on the wing-body combination were obtained at angles of attack from 0 to 26 degrees at Mach numbers from 0.80 to 0.98 and from 0 to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic chord, varied from 7,000,000 to 8,500,000 over the test Mach number range.
Author : William C. Sleeman
Publisher : Unknown
Page : 36 pages
File Size : 52,5 Mb
Release : 1949
Category : Aerodynamics, Transonic
ISBN : UOM:39015086464610
Author : Adam Chehouri
Publisher : GRIN Verlag
Page : 72 pages
File Size : 50,5 Mb
Release : 2014-01-13
Category : Technology & Engineering
ISBN : 9783656572541
Master's Thesis from the year 2013 in the subject Engineering - Mechanical Engineering, grade: 4.06/4.5 GPa, , language: English, abstract: In the wind industry, the current trend is towards building larger and larger turbines. This presents additional structural challenges and requires blade materials that are both lighter and stiffer than the ones presently used. This work is aimed to aid the work of designing new wind turbine blades by providing a comparative study of different composite materials. A coupled Finite-Element-Method (FEM) - Blade Element Momentum (BEM) code was used to simulate the aerodynamic forces subjected on the blade. The developed BEM code was written using LabView allowing an iterative numerical approach solver taking into the consideration the unsteady aerodynamic effects and off –design performance issues such as Tip Loss, Hub Loss and Turbulent Wake State therefore developing a more rational aerodynamic model. For this thesis, the finite element study was conducted on the Static Structural Workbench of ANSYS, as for the geometry of the blade it was imported from a previous study prepared by Cornell University. Confirmation of the performance analysis of the chosen wind turbine blade are presented and discussed blade including the generated power, tip deflection, thrust and tangential force for a steady flow of 8m/s. The elastic and ultimate strength properties were provided by Hallal et al. The Tsai- Hill and Hoffman failure criterions were both conducted to the resulting stresses and shears for each blade composite material structure to determine the presence of static rupture. A progressive fatigue damage model was conducted to simulate the fatigue behavior of laminated composite materials, an algorithm developed by Shokrieh. It is concluded that with respect to a material blade design cycle, the coupling between a finite element package and blade element and momentum code under steady and static conditions can be useful. Especially when an integration between this coupled approach and a dynamic simulation tool could be established, a more advanced flexible blade design can be then analyzed for a novel generation of more flexible wind turbine blades.
Author : Anonim
Publisher : Unknown
Page : 524 pages
File Size : 54,6 Mb
Release : 1949
Category : Electronic
ISBN : NASA:31769000528763
Author : JACK F. RUNCKEL,EDWIN E. JR. LEE,NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C.
Publisher : Unknown
Page : 1 pages
File Size : 44,9 Mb
Release : 1961
Category : Electronic
ISBN : OCLC:227261890
An investigation at transonic speeds of the loading over a 45 degree sweptback wing having an aspect ratio of 3, a taper ratio of 0.2, and NACA 65A004 airfoil sections was conducted in the Langley 16-foot transonic tunnel. Pressure measurements on the wing-body combi ation were obtained at angles of attack from 0 degrees to 26 degrees at Mach numbers from 0.80 to 0.98 and at angles of attack from 0 degrees to about 12 degrees at Mach numbers from 1.00 to 1.05. Reynolds number, based on the wing mean aerodynamic c ord varied from 7 times 10 to the 6th po er to 8.5 times 10 to the 6th power over the test Mach number range. Results of the investigation indicate that a highly swept shock originates at the juncture of the wing leading edge and the body at moderate angles of attack and has a large influence on the loading over the inboard wing sections. (Author).