Add to ORKGA method was devised for estimating the incompressible-flow pressure distribution over compressor blade sections at design angle of attack. The theoretical incremental velocities due to camber and thickness of the section as an isolated airfoil are assumed proportional to the average passage velocity and are modified by empirically determined interference factors. Comparisons were made between estimated and test pressure distributions of NACA 65-series sections for typical conditions. Good agreement was obtained
Current literature on the three dimensional flow through compressor cascades deals with a row of rot...
Conducting full annulus experiments on multistage compressors is costly and time consuming due to th...
Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June ...
A method was devised for estimating the incompressible-flow pressure distribution over compressor bl...
Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
Development of a method of estimating deviation angles by analytical procedures was begun. Solutions...
The conventional methods for the design of the blades in the case of axial turbomachines are conside...
Linearized analyses have been carried out for the induced velocity and pressure fields within a comp...
A blade-element theory for axial-flow compressors has been developed and applied to the analysis of ...
An investigation has been made in the Langley 16-foot high-speed tunnel to determine the propeller-s...
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
Current literature on the three dimensional flow through compressor cascades deals with a row of rot...
Conducting full annulus experiments on multistage compressors is costly and time consuming due to th...
Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June ...
A method was devised for estimating the incompressible-flow pressure distribution over compressor bl...
Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
Development of a method of estimating deviation angles by analytical procedures was begun. Solutions...
The conventional methods for the design of the blades in the case of axial turbomachines are conside...
Linearized analyses have been carried out for the induced velocity and pressure fields within a comp...
A blade-element theory for axial-flow compressors has been developed and applied to the analysis of ...
An investigation has been made in the Langley 16-foot high-speed tunnel to determine the propeller-s...
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
Current literature on the three dimensional flow through compressor cascades deals with a row of rot...
Conducting full annulus experiments on multistage compressors is costly and time consuming due to th...
Presented at the International Gas Turbine and Aeroengine Congress and Exposition Orlando, FL June ...