درباره ما
NACA-RM-L54I13
Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotor blade-setting angles at solidities. of 1.0 and 0.5
Year: 1954
Abstract: INTRODUCTION
Two-dimensional cascade data obtained in a porous-wall test facility are extensively used in the design of axial-flow compressors. Since the flow in axial-flow compressors is three-dimensional, a correlation between cascade and compressor-rotor data is required. Pressure distributions and turning angles measured for a rotor have been shown in reference 1 to be similar to those measured in cascade at the design angle of attack. Reference 2 indicates that rotor performance data can be estimated accurately from cascade data for a wide variety of conditions. The purpose of the present investigation is to further the establishment of a correlation between low-speed cascade and compressor-rotor data over a wide range of blade-setting angles.
A rotor having medium-camber NACA 65-series airfoil sections, was tested without guide vanes or stators over a wide range of blade-setting angles in a low-speed 28-inch test blower. Measured overall and blade-element performance values were compared with values estimated by using two-dimensional porous-wall cascade data. To facilitate this work, the rotor was designed with constant solidity along the radius.
Two-dimensional cascade data obtained in a porous-wall test facility are extensively used in the design of axial-flow compressors. Since the flow in axial-flow compressors is three-dimensional, a correlation between cascade and compressor-rotor data is required. Pressure distributions and turning angles measured for a rotor have been shown in reference 1 to be similar to those measured in cascade at the design angle of attack. Reference 2 indicates that rotor performance data can be estimated accurately from cascade data for a wide variety of conditions. The purpose of the present investigation is to further the establishment of a correlation between low-speed cascade and compressor-rotor data over a wide range of blade-setting angles.
A rotor having medium-camber NACA 65-series airfoil sections, was tested without guide vanes or stators over a wide range of blade-setting angles in a low-speed 28-inch test blower. Measured overall and blade-element performance values were compared with values estimated by using two-dimensional porous-wall cascade data. To facilitate this work, the rotor was designed with constant solidity along the radius.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:10:30Z | |
| date available | 2017-09-04T17:10:30Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | YPSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/133991 | |
| description abstract | INTRODUCTION Two-dimensional cascade data obtained in a porous-wall test facility are extensively used in the design of axial-flow compressors. Since the flow in axial-flow compressors is three-dimensional, a correlation between cascade and compressor-rotor data is required. Pressure distributions and turning angles measured for a rotor have been shown in reference 1 to be similar to those measured in cascade at the design angle of attack. Reference 2 indicates that rotor performance data can be estimated accurately from cascade data for a wide variety of conditions. The purpose of the present investigation is to further the establishment of a correlation between low-speed cascade and compressor-rotor data over a wide range of blade-setting angles. A rotor having medium-camber NACA 65-series airfoil sections, was tested without guide vanes or stators over a wide range of blade-setting angles in a low-speed 28-inch test blower. Measured overall and blade-element performance values were compared with values estimated by using two-dimensional porous-wall cascade data. To facilitate this work, the rotor was designed with constant solidity along the radius. | |
| language | English | |
| title | NACA-RM-L54I13 | num |
| title | Comparison of low-speed rotor and cascade performance for medium-camber NACA 65-(C(sub lo)A(sub 10) 10 compressor-blade sections over a wide range of rotor blade-setting angles at solidities. of 1.0 and 0.5 | en |
| type | standard | |
| page | 42 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |