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NACA-RM-A51J11
The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil
Year: 1951
Abstract: INTRODUCTION
At supersonic mach numbers, the airfoil section having minimum drag for a prescribed structural strength or stiffness may have a blunt trailing edge, as has been shown through theoretical considerations by Chapman in reference 1. The two dimensional characteristics of such airfoils of moderate thickness as compared with a more conventional airfoil having a sharp trailing edge have been investigated experimentally at subsonic mach numbers (reference 2). Although the results of that investigation indicated higher minimum drag for the blunt-trailing slope increased at mach numbers where the lift-curve slope decreased for the sharp-trailing-edge airfoil. Thus, it would seem that blunt trailing-edge airfoils may be of some practical value at both both subsonic and supersonic mach numbers.
The present investigation was undertaken to evaluate the effect of an increase in trailing-edge thickness on the aerodynamic characteristics of a thin three-dimensional wing in the transonic mach number range. For this investigation the thick trailing-edge airfoils were formed by building up the trailing edge to the desired thickness and then fairing to the original airfoil by straight lines. The forward portion of the circular-arc section remained intact and the resulting airfoil was not one of the optimum sections derived in reference 1.
At supersonic mach numbers, the airfoil section having minimum drag for a prescribed structural strength or stiffness may have a blunt trailing edge, as has been shown through theoretical considerations by Chapman in reference 1. The two dimensional characteristics of such airfoils of moderate thickness as compared with a more conventional airfoil having a sharp trailing edge have been investigated experimentally at subsonic mach numbers (reference 2). Although the results of that investigation indicated higher minimum drag for the blunt-trailing slope increased at mach numbers where the lift-curve slope decreased for the sharp-trailing-edge airfoil. Thus, it would seem that blunt trailing-edge airfoils may be of some practical value at both both subsonic and supersonic mach numbers.
The present investigation was undertaken to evaluate the effect of an increase in trailing-edge thickness on the aerodynamic characteristics of a thin three-dimensional wing in the transonic mach number range. For this investigation the thick trailing-edge airfoils were formed by building up the trailing edge to the desired thickness and then fairing to the original airfoil by straight lines. The forward portion of the circular-arc section remained intact and the resulting airfoil was not one of the optimum sections derived in reference 1.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:11:57Z | |
| date available | 2017-09-04T16:11:57Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | SNMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/75164 | |
| description abstract | INTRODUCTION At supersonic mach numbers, the airfoil section having minimum drag for a prescribed structural strength or stiffness may have a blunt trailing edge, as has been shown through theoretical considerations by Chapman in reference 1. The two dimensional characteristics of such airfoils of moderate thickness as compared with a more conventional airfoil having a sharp trailing edge have been investigated experimentally at subsonic mach numbers (reference 2). Although the results of that investigation indicated higher minimum drag for the blunt-trailing slope increased at mach numbers where the lift-curve slope decreased for the sharp-trailing-edge airfoil. Thus, it would seem that blunt trailing-edge airfoils may be of some practical value at both both subsonic and supersonic mach numbers. The present investigation was undertaken to evaluate the effect of an increase in trailing-edge thickness on the aerodynamic characteristics of a thin three-dimensional wing in the transonic mach number range. For this investigation the thick trailing-edge airfoils were formed by building up the trailing edge to the desired thickness and then fairing to the original airfoil by straight lines. The forward portion of the circular-arc section remained intact and the resulting airfoil was not one of the optimum sections derived in reference 1. | |
| language | English | |
| title | NACA-RM-A51J11 | num |
| title | The effects at transonic speeds of thickening the trailing edge of a wing with a 4-percent-thick circular-arc airfoil | en |
| type | standard | |
| page | 44 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |