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NACA-RM-A55D11
Investigation of the effects of an airfoil section modification on the aerodynamic characteristics at subsonic and supersonic speeds of a thin swept wing of aspect ratio 3 in combination with a body
Year: 1955
Abstract: INTRODUCTION
The adverse effects of wing-tip stall on the low-speed stability and drag characteristics of swept-wing airplanes are widely recognized. To delay wing-tip stall to higher lift coefficients, the use of large increases in leading-edge radius together with slight amounts of forward camber has been shown to be effective on wings of moderate thickness (refs. 1 to 3). However, there appear to be Tuttle data on the high speed effects of such modifications on wing-body combinations, and not any data at all on their effects on thin wings.
The purpose of the investigation reported herein was to evaluate the effects of such a modification cm a thin swept wing of low aspect ratio k combination with a body at both subsonic and supersonic speeds. The modified airfoil section was designed to attain a given low-speed clmax, comparable to that which might be expected from leading-edge flaps. The experimental three-dimensional results, obtained at several Reynolds numbers, are presented and discussed from both the low-speed and high-speed standpoints. The measured low-speed characteristic are compared with predictions based on simple-sweep theory applied to the two-dimensional wing section characteristics. The measured transonic drag rise at zero lift is compared with values of-wave drag computed by linearized theory.
The adverse effects of wing-tip stall on the low-speed stability and drag characteristics of swept-wing airplanes are widely recognized. To delay wing-tip stall to higher lift coefficients, the use of large increases in leading-edge radius together with slight amounts of forward camber has been shown to be effective on wings of moderate thickness (refs. 1 to 3). However, there appear to be Tuttle data on the high speed effects of such modifications on wing-body combinations, and not any data at all on their effects on thin wings.
The purpose of the investigation reported herein was to evaluate the effects of such a modification cm a thin swept wing of low aspect ratio k combination with a body at both subsonic and supersonic speeds. The modified airfoil section was designed to attain a given low-speed clmax, comparable to that which might be expected from leading-edge flaps. The experimental three-dimensional results, obtained at several Reynolds numbers, are presented and discussed from both the low-speed and high-speed standpoints. The measured low-speed characteristic are compared with predictions based on simple-sweep theory applied to the two-dimensional wing section characteristics. The measured transonic drag rise at zero lift is compared with values of-wave drag computed by linearized theory.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:08:47Z | |
| date available | 2017-09-04T16:08:47Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | BIMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/72057 | |
| description abstract | INTRODUCTION The adverse effects of wing-tip stall on the low-speed stability and drag characteristics of swept-wing airplanes are widely recognized. To delay wing-tip stall to higher lift coefficients, the use of large increases in leading-edge radius together with slight amounts of forward camber has been shown to be effective on wings of moderate thickness (refs. 1 to 3). However, there appear to be Tuttle data on the high speed effects of such modifications on wing-body combinations, and not any data at all on their effects on thin wings. The purpose of the investigation reported herein was to evaluate the effects of such a modification cm a thin swept wing of low aspect ratio k combination with a body at both subsonic and supersonic speeds. The modified airfoil section was designed to attain a given low-speed clmax, comparable to that which might be expected from leading-edge flaps. The experimental three-dimensional results, obtained at several Reynolds numbers, are presented and discussed from both the low-speed and high-speed standpoints. The measured low-speed characteristic are compared with predictions based on simple-sweep theory applied to the two-dimensional wing section characteristics. The measured transonic drag rise at zero lift is compared with values of-wave drag computed by linearized theory. | |
| language | English | |
| title | NACA-RM-A55D11 | num |
| title | Investigation of the effects of an airfoil section modification on the aerodynamic characteristics at subsonic and supersonic speeds of a thin swept wing of aspect ratio 3 in combination with a body | en |
| type | standard | |
| page | 47 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |