درباره ما
NACA-TN-1546
Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8
Year: 1948
Abstract: INTRODUCTION
The NACA 16-series airfoils were derived (reference 1) for use at high speeds, particularly for propeller applications. The variations in design camber and thickness ration, covered in reference 1, were not of sufficient scope to meet all the requirements of propeller design. A test program was formulated, therefore, whereby the aerodynamic characteristics would be obtained for some of the airfoils of reference 1 over an extended angular range, as well as for 12 additional airfoils of the same series. The results of this investigation combined with the data of reference 1 are presented herein uncorrected for tunnel-wall constriction effects. The magnitude of the constriction effect on Mach number at supercritical speeds is approximately 2 percent of the uncorrected value and does not affect the validity of the conclusions.
The NACA 16-series airfoils were derived (reference 1) for use at high speeds, particularly for propeller applications. The variations in design camber and thickness ration, covered in reference 1, were not of sufficient scope to meet all the requirements of propeller design. A test program was formulated, therefore, whereby the aerodynamic characteristics would be obtained for some of the airfoils of reference 1 over an extended angular range, as well as for 12 additional airfoils of the same series. The results of this investigation combined with the data of reference 1 are presented herein uncorrected for tunnel-wall constriction effects. The magnitude of the constriction effect on Mach number at supercritical speeds is approximately 2 percent of the uncorrected value and does not affect the validity of the conclusions.
Subject: AIRFOILS
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:25:20Z | |
| date available | 2017-09-04T15:25:20Z | |
| date copyright | 01/01/1948 | |
| date issued | 1948 | |
| identifier other | NKZSYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/25874 | |
| description abstract | INTRODUCTION The NACA 16-series airfoils were derived (reference 1) for use at high speeds, particularly for propeller applications. The variations in design camber and thickness ration, covered in reference 1, were not of sufficient scope to meet all the requirements of propeller design. A test program was formulated, therefore, whereby the aerodynamic characteristics would be obtained for some of the airfoils of reference 1 over an extended angular range, as well as for 12 additional airfoils of the same series. The results of this investigation combined with the data of reference 1 are presented herein uncorrected for tunnel-wall constriction effects. The magnitude of the constriction effect on Mach number at supercritical speeds is approximately 2 percent of the uncorrected value and does not affect the validity of the conclusions. | |
| language | English | |
| title | NACA-TN-1546 | num |
| title | Aerodynamics characteristics of 24 NACA 16-series airfoils at Mach numbers between 0.3 and 0.8 | en |
| type | standard | |
| page | 90 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1948 | |
| contenttype | fulltext | |
| subject keywords | AIRFOILS | |
| subject keywords | CHAR | |
| subject keywords | MOMENTS | |
| subject keywords | NACA | |
| subject keywords | ORDINATES | |
| subject keywords | PROPELLER | |
| subject keywords | SERIES |