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NACA-TN-1046
Preliminary wind-tunnel investigation at low speed of stability and control characteristics of swept-back wings
Year: 1946
Abstract: INTRODUCTION
Much interest has been shown in the possibility of using wings with large amounts of sweepback for high-speed missiles and aircraft. Analyses presented in references 1 and 2 show that the lift on a swept-back wing depends primarily on the component of velocity normal to the wing leading edge. Reference 3 shows that this component of velocity also is a most important factor in determining compressibility effects and points out that, from consideration of compressibility, the critical flight Mach number of a swept-back wing should be higher than that of an unswept wing. In order to minimize the adverse effects of compressibility at high Mach numbers, the angle of sweep should be such that the component of velocity normal to the leading edge does not exceed that corresponding to the critical Mach number of the airfoil sections.
Since very little data are available on wings having angles of sweep greater than 30, tests of an exploratory nature were made of wings having angles of sweepback of 0°, 30°, 45°, and 60°. These tests were made in the 6- by 6-foot test section of the Langley stability tunnel to investigate at low speeds the stability and control characteristics of swept-back wings. The effect of sweepback on the effectiveness of an aileron, a split flap, and a spoiler was investigated for each sweepback angle tested. The effect of a drooped tip was investigated for the 45 swept-back wing, and the effect of increased aspect ratio as investigated for the 0° and 45° swept-back wings.
Although these tests were made at low airspeeds, the data are also of importance in application to transonic speed because, as pointed out in reference 3, if the wings are designed with proper sweep, the wing will have the same characteristics as at sub critical speed.
Much interest has been shown in the possibility of using wings with large amounts of sweepback for high-speed missiles and aircraft. Analyses presented in references 1 and 2 show that the lift on a swept-back wing depends primarily on the component of velocity normal to the wing leading edge. Reference 3 shows that this component of velocity also is a most important factor in determining compressibility effects and points out that, from consideration of compressibility, the critical flight Mach number of a swept-back wing should be higher than that of an unswept wing. In order to minimize the adverse effects of compressibility at high Mach numbers, the angle of sweep should be such that the component of velocity normal to the leading edge does not exceed that corresponding to the critical Mach number of the airfoil sections.
Since very little data are available on wings having angles of sweep greater than 30, tests of an exploratory nature were made of wings having angles of sweepback of 0°, 30°, 45°, and 60°. These tests were made in the 6- by 6-foot test section of the Langley stability tunnel to investigate at low speeds the stability and control characteristics of swept-back wings. The effect of sweepback on the effectiveness of an aileron, a split flap, and a spoiler was investigated for each sweepback angle tested. The effect of a drooped tip was investigated for the 45 swept-back wing, and the effect of increased aspect ratio as investigated for the 0° and 45° swept-back wings.
Although these tests were made at low airspeeds, the data are also of importance in application to transonic speed because, as pointed out in reference 3, if the wings are designed with proper sweep, the wing will have the same characteristics as at sub critical speed.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:10:38Z | |
| date available | 2017-09-04T16:10:38Z | |
| date copyright | 01/01/1946 | |
| date issued | 1946 | |
| identifier other | SJYIYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/73888 | |
| description abstract | INTRODUCTION Much interest has been shown in the possibility of using wings with large amounts of sweepback for high-speed missiles and aircraft. Analyses presented in references 1 and 2 show that the lift on a swept-back wing depends primarily on the component of velocity normal to the wing leading edge. Reference 3 shows that this component of velocity also is a most important factor in determining compressibility effects and points out that, from consideration of compressibility, the critical flight Mach number of a swept-back wing should be higher than that of an unswept wing. In order to minimize the adverse effects of compressibility at high Mach numbers, the angle of sweep should be such that the component of velocity normal to the leading edge does not exceed that corresponding to the critical Mach number of the airfoil sections. Since very little data are available on wings having angles of sweep greater than 30, tests of an exploratory nature were made of wings having angles of sweepback of 0°, 30°, 45°, and 60°. These tests were made in the 6- by 6-foot test section of the Langley stability tunnel to investigate at low speeds the stability and control characteristics of swept-back wings. The effect of sweepback on the effectiveness of an aileron, a split flap, and a spoiler was investigated for each sweepback angle tested. The effect of a drooped tip was investigated for the 45 swept-back wing, and the effect of increased aspect ratio as investigated for the 0° and 45° swept-back wings. Although these tests were made at low airspeeds, the data are also of importance in application to transonic speed because, as pointed out in reference 3, if the wings are designed with proper sweep, the wing will have the same characteristics as at sub critical speed. | |
| language | English | |
| title | NACA-TN-1046 | num |
| title | Preliminary wind-tunnel investigation at low speed of stability and control characteristics of swept-back wings | en |
| type | standard | |
| page | 70 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1946 | |
| contenttype | fulltext |