Add to ORKGAn investigation has been conducted to compare the performance of NACA 65-series compressor blades in two-dimensional cascade with that in an axial flow compressor. Blade pressure distributions were obtained by the use of a mercury-seal pressure-transfer device. The comparison indicated that cascade data accurately predicted the turning angle and blade pressure distribution obtained in the compressor at design conditions
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
A method was devised for estimating the incompressible-flow pressure distribution over compressor bl...
A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet M...
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speed...
A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...
Available experimental two-dimensional-cascade data for conventional compressor blade sections are c...
The performance of NACA 65-series compressor blade sections in cascade has been investigated systema...
Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...
The performance of NACA 65-series compressor blade section in cascade has been investigated systemat...
Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial st...
For use in computing the detailed performance parameters of individual blade rows of a multistage co...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
A complete stage of an axial-flow compressor was designed and built to investigate the possibility o...
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
A method was devised for estimating the incompressible-flow pressure distribution over compressor bl...
A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet M...
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speed...
A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...
Available experimental two-dimensional-cascade data for conventional compressor blade sections are c...
The performance of NACA 65-series compressor blade sections in cascade has been investigated systema...
Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...
The performance of NACA 65-series compressor blade section in cascade has been investigated systemat...
Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial st...
For use in computing the detailed performance parameters of individual blade rows of a multistage co...
A 30-inch tip-diameter axial-flow compressor stage was investigated with and without rotor to determ...
A complete stage of an axial-flow compressor was designed and built to investigate the possibility o...
AbstractThe base of this paper is to find the pressure distribution over the compressor blades throu...
A method was devised for estimating the incompressible-flow pressure distribution over compressor bl...
A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet M...