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NACA-TR-1031
A study of the use of experimental stability derivatives in the calculation of the lateral disturbed motions of a swept-wing airplane and comparison with flight results
Year: 1951
Abstract: An investigation was made to determine the accuracy with which the lateral flight motions of a swept-wing airplane could be predicted from experimental stability derivatives determined in the 6-foot-diameter rolling-flow test section and 6- by 6-foot curved-flow test section of the Langley stability tunnel. In addition determination of the significance of including the nonlinear aerodynamic effects of sideslip in the calculations of the motions was desired. All experimental aerodynamic data necessary for prediction of the lateral flight motions are presented along with a number of comparisons between flight and calculated motions caused by rudder and aileron disturbances.
In general, the agreement between the calculated and measured motions of the airplane considered was good when the effects of all control movements were taken into account. the greatest disagreement occurred at lift coefficients where Reynolds number effects on the experimental derivatives would be expected to be high, which for the case considered was for lift coefficients above about 0.8 when wing slots were used. The nonlinear effects of sideslip for this airplane were not very significant for the motions considered, which generally involved sideslip angles less than 10º.
In general, the agreement between the calculated and measured motions of the airplane considered was good when the effects of all control movements were taken into account. the greatest disagreement occurred at lift coefficients where Reynolds number effects on the experimental derivatives would be expected to be high, which for the case considered was for lift coefficients above about 0.8 when wing slots were used. The nonlinear effects of sideslip for this airplane were not very significant for the motions considered, which generally involved sideslip angles less than 10º.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:00:39Z | |
| date available | 2017-09-04T17:00:39Z | |
| date copyright | 01/01/1951 | |
| date issued | 1951 | |
| identifier other | XPDZYDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/124143 | |
| description abstract | An investigation was made to determine the accuracy with which the lateral flight motions of a swept-wing airplane could be predicted from experimental stability derivatives determined in the 6-foot-diameter rolling-flow test section and 6- by 6-foot curved-flow test section of the Langley stability tunnel. In addition determination of the significance of including the nonlinear aerodynamic effects of sideslip in the calculations of the motions was desired. All experimental aerodynamic data necessary for prediction of the lateral flight motions are presented along with a number of comparisons between flight and calculated motions caused by rudder and aileron disturbances. In general, the agreement between the calculated and measured motions of the airplane considered was good when the effects of all control movements were taken into account. the greatest disagreement occurred at lift coefficients where Reynolds number effects on the experimental derivatives would be expected to be high, which for the case considered was for lift coefficients above about 0.8 when wing slots were used. The nonlinear effects of sideslip for this airplane were not very significant for the motions considered, which generally involved sideslip angles less than 10º. | |
| language | English | |
| title | NACA-TR-1031 | num |
| title | A study of the use of experimental stability derivatives in the calculation of the lateral disturbed motions of a swept-wing airplane and comparison with flight results | en |
| type | standard | |
| page | 28 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1951 | |
| contenttype | fulltext |