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NACA-TN-3551
Experimental investigation at low speed of effects of fuselage cross section on static longitudinal and lateral stability characteristics of models having 0 degrees and 45 degrees sweptback surfaces
Year: 1955
Abstract: An experiment investigation at low speed was made to determine the effects of fuselage cross section on the static longitudinal and lateral stability characteristics of midwing airplane models having 00 and 450 sweptback surfaces. The results indicated that the main effects of fuselage cross section on the longitudinal and directional stability characteristics of the models at low angels of attack are caused by the direct contributions of the fuselage. At the high angels of attack, in addition to the direct contributions of the fuselage, wing-fuselage interference (sidewash) with the tail decreases the tail contributions to the directional stability. The configuration consisting of the wing and deep fuselage produced the most detrimental effect, and the configuration consisting of the wing and shallow fuselage was the least detrimental in this respect. For the complete configurations tested, fuselage cross section had little effect on the range of linearity of the curves of yawing moment against sideslip angle for the angles of attack and sideslip investigated. In general, the configuration with the deep fuselage had the poorest directional characteristics of the models investigated.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:30:16Z | |
| date available | 2017-09-04T15:30:16Z | |
| date copyright | 01/01/1955 | |
| date issued | 1955 | |
| identifier other | AWNUYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/31601 | |
| description abstract | An experiment investigation at low speed was made to determine the effects of fuselage cross section on the static longitudinal and lateral stability characteristics of midwing airplane models having 00 and 450 sweptback surfaces. The results indicated that the main effects of fuselage cross section on the longitudinal and directional stability characteristics of the models at low angels of attack are caused by the direct contributions of the fuselage. At the high angels of attack, in addition to the direct contributions of the fuselage, wing-fuselage interference (sidewash) with the tail decreases the tail contributions to the directional stability. The configuration consisting of the wing and deep fuselage produced the most detrimental effect, and the configuration consisting of the wing and shallow fuselage was the least detrimental in this respect. For the complete configurations tested, fuselage cross section had little effect on the range of linearity of the curves of yawing moment against sideslip angle for the angles of attack and sideslip investigated. In general, the configuration with the deep fuselage had the poorest directional characteristics of the models investigated. | |
| language | English | |
| title | NACA-TN-3551 | num |
| title | Experimental investigation at low speed of effects of fuselage cross section on static longitudinal and lateral stability characteristics of models having 0 degrees and 45 degrees sweptback surfaces | en |
| type | standard | |
| page | 46 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1955 | |
| contenttype | fulltext |