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NACA-RM-A53L22
An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0.6, 0.9, 1.4, and 1.7
Year: 1954
Abstract: INTRODUCTION
One of the difficult problems associated with the design of aircraft with triangular wings is concerned with the lateral-directional flying qualities. The difficulties arise from the large variations of dihedral effect and directional stability with lift coefficient. Major factors influencing these characteristics are the contributions of the wing and the vertical tail. Linear theoretical methods for predicting the effects of wing aspect ratio are available (ref. 1) but largely unsubstantiated.
In order to verify these theoretical methods and investigate their applicability to wing-body combinations, the characteristics of several of the triangular-wing models utilized in the investigation of reference 2 were studied in sideslip. The present report is concerned with these results which show, to a limited extent, the influence of aspect ratio, thickness ratio, and camber and twist on the rolling moments, yawing moments, and side forces due to sideslip.
One of the difficult problems associated with the design of aircraft with triangular wings is concerned with the lateral-directional flying qualities. The difficulties arise from the large variations of dihedral effect and directional stability with lift coefficient. Major factors influencing these characteristics are the contributions of the wing and the vertical tail. Linear theoretical methods for predicting the effects of wing aspect ratio are available (ref. 1) but largely unsubstantiated.
In order to verify these theoretical methods and investigate their applicability to wing-body combinations, the characteristics of several of the triangular-wing models utilized in the investigation of reference 2 were studied in sideslip. The present report is concerned with these results which show, to a limited extent, the influence of aspect ratio, thickness ratio, and camber and twist on the rolling moments, yawing moments, and side forces due to sideslip.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:59:48Z | |
| date available | 2017-09-04T15:59:48Z | |
| date copyright | 01/01/1954 | |
| date issued | 1954 | |
| identifier other | RGMCWDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/62952 | |
| description abstract | INTRODUCTION One of the difficult problems associated with the design of aircraft with triangular wings is concerned with the lateral-directional flying qualities. The difficulties arise from the large variations of dihedral effect and directional stability with lift coefficient. Major factors influencing these characteristics are the contributions of the wing and the vertical tail. Linear theoretical methods for predicting the effects of wing aspect ratio are available (ref. 1) but largely unsubstantiated. In order to verify these theoretical methods and investigate their applicability to wing-body combinations, the characteristics of several of the triangular-wing models utilized in the investigation of reference 2 were studied in sideslip. The present report is concerned with these results which show, to a limited extent, the influence of aspect ratio, thickness ratio, and camber and twist on the rolling moments, yawing moments, and side forces due to sideslip. | |
| language | English | |
| title | NACA-RM-A53L22 | num |
| title | An experimental investigation of four triangular-wing-body combinations in sideslip at Mach numbers 0.6, 0.9, 1.4, and 1.7 | en |
| type | standard | |
| page | 18 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1954 | |
| contenttype | fulltext |