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NACA-TN-3554
A preliminary investigation of the effects of frequency and amplitude on the rolling derivatives of an unswept-wing model oscillating in roll
Year: 1956
Abstract: A model with separable wing and tail assembly was oscillated in roll through a range of frequencies and amplitudes of oscillation for an angle of attack of 0° and at one frequency and amplitude for two higher angles of attack in order to determine the effects of the unsteady motion on the rolling stability derivatives of the model and its components.
A variation of frequency or amplitude of oscillation in the range covered at an angle of attack of 0° had no important effect on either the yawing moment due to rolling or the damping in roll for this unsweptwing airplane configuration". The only appreciable value of yawing moment due to rolling was shown by the fuselage-tail combination. This configuration experienced a reduction in magnitude of the derivative as either the frequency or the amplitude of the oscillation increased.
The values of the rolling derivatives obtained by oscillation were consistent with the values measured by means of conventional rolling flow tests at an single of attack of 0°. For the model with the wing at a high angle of attack, the oscillatory yawing moment due to rolling was different from that obtained under steady-state conditions.
A variation of frequency or amplitude of oscillation in the range covered at an angle of attack of 0° had no important effect on either the yawing moment due to rolling or the damping in roll for this unsweptwing airplane configuration". The only appreciable value of yawing moment due to rolling was shown by the fuselage-tail combination. This configuration experienced a reduction in magnitude of the derivative as either the frequency or the amplitude of the oscillation increased.
The values of the rolling derivatives obtained by oscillation were consistent with the values measured by means of conventional rolling flow tests at an single of attack of 0°. For the model with the wing at a high angle of attack, the oscillatory yawing moment due to rolling was different from that obtained under steady-state conditions.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:41:00Z | |
| date available | 2017-09-04T17:41:00Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | DWNUYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/163905 | |
| description abstract | A model with separable wing and tail assembly was oscillated in roll through a range of frequencies and amplitudes of oscillation for an angle of attack of 0° and at one frequency and amplitude for two higher angles of attack in order to determine the effects of the unsteady motion on the rolling stability derivatives of the model and its components. A variation of frequency or amplitude of oscillation in the range covered at an angle of attack of 0° had no important effect on either the yawing moment due to rolling or the damping in roll for this unsweptwing airplane configuration". The only appreciable value of yawing moment due to rolling was shown by the fuselage-tail combination. This configuration experienced a reduction in magnitude of the derivative as either the frequency or the amplitude of the oscillation increased. The values of the rolling derivatives obtained by oscillation were consistent with the values measured by means of conventional rolling flow tests at an single of attack of 0°. For the model with the wing at a high angle of attack, the oscillatory yawing moment due to rolling was different from that obtained under steady-state conditions. | |
| language | English | |
| title | NACA-TN-3554 | num |
| title | A preliminary investigation of the effects of frequency and amplitude on the rolling derivatives of an unswept-wing model oscillating in roll | en |
| type | standard | |
| page | 28 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |