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NACA-RM-L8K12
Lateral-control investigation on a 37 degrees sweptback wing of aspect ratio 6 at a Reynolds number of 6,800,000
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:19:17Z | |
| date available | 2017-09-04T18:19:17Z | |
| date copyright | 01/01/1949 | |
| date issued | 1949 | |
| identifier other | HTSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/202011 | |
| description abstract | INTRODUCTION The use of sweptback wings on high-speed airplanes introduces several stability and control problems in the low-speed range. Two of these problems are unstable pitching moments and loss of lateral control at the stall. Both of these problems result from the characteristic of sweptback wings to stall first at the tips. Several devices have been found to delay the tip stall until an inboard stall has developed so that stable pitching moments were obtained at the stall. (See references 1 and 2.) These devices were leading-edge flap, leading-edge slat, and drooped leading edge on the outer portion of the wing. In order to determine the effects of these devices on the lateral-control characteristics of a sweptback wing, an investigation was carried out on a 37° sweptback semispan wing of aspect ratio 6. The investigation included the determination of (a) the control and hinge-moment characteristics of a half-span 20-percent-chord aileron, (b) the control characteristics of two configurations of spoilers, and (c) the effects of high-lift and stall-control devices on the characteristics of the aileron and spoilers. | |
| language | English | |
| title | NACA-RM-L8K12 | num |
| title | Lateral-control investigation on a 37 degrees sweptback wing of aspect ratio 6 at a Reynolds number of 6,800,000 | en |
| type | standard | |
| page | 60 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1949 | |
| contenttype | fulltext |
