Add to ORKGA two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish the performance of the NACA 65-series compressor blade sections over the useful range of inlet angle, solidity, and section camber. Design points for optimum high-speed operation are presented. The loading limitation is determined for some conditions. Trends of section operating range with increasing section camber are determined for the four inlet angles tested
An investigation has been conducted to determine the influence of aspect ratio, boundary-layer contr...
Windmilling tests on a two-stage transonic compressor with a design over-all pressure ratio of 1.85 ...
A 65-(12)10 compressor blade cascade was evaluated at design geometry for Mach numbers from 0.12 to ...
The performance of NACA 65-series compressor blade sections in cascade has been investigated systema...
The performance of NACA 65-series compressor blade section in cascade has been investigated systemat...
A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...
Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...
Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade s...
A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speed...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...
A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet M...
A complete stage of an axial-flow compressor was designed and built to investigate the possibility o...
Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial st...
The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blad...
An investigation has been conducted to determine the influence of aspect ratio, boundary-layer contr...
Windmilling tests on a two-stage transonic compressor with a design over-all pressure ratio of 1.85 ...
A 65-(12)10 compressor blade cascade was evaluated at design geometry for Mach numbers from 0.12 to ...
The performance of NACA 65-series compressor blade sections in cascade has been investigated systema...
The performance of NACA 65-series compressor blade section in cascade has been investigated systemat...
A two-dimensional low-speed porous-wall cascade tunnel investigation has been conducted to establish...
Six percent thick NACA 63-series compressor-blade sections having a loaded leading-edge A4K6 mean li...
Two-dimensional porous-well cascade tests of the NACA 65- (l2Al0) 10 and NACA 65-(l2A2I8b)10 blade s...
A typical axial-flow compressor rotor using NACA 65-series compressor blades was tested at low speed...
An investigation has been conducted to compare the performance of NACA 65-series compressor blades i...
The comparison indicated that cascade data accurately predicted the turning angle and blade pressure...
A cascade of 65-(12)10 compressor blades was tested at one geometric setting over a range of inlet M...
A complete stage of an axial-flow compressor was designed and built to investigate the possibility o...
Total-pressure deficiency for an annular cascade of 65-(12)10 blades was measured at three radial st...
The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blad...
An investigation has been conducted to determine the influence of aspect ratio, boundary-layer contr...
Windmilling tests on a two-stage transonic compressor with a design over-all pressure ratio of 1.85 ...
A 65-(12)10 compressor blade cascade was evaluated at design geometry for Mach numbers from 0.12 to ...