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NACA-RM-L57A30
Experimental determination at subsonic speeds of the oscillatory and static lateral stability derivatives of a series of delta wings with leading-edge sweep from 30 degrees to 86.5 degrees
Year: 1957
Abstract: INTRODUCTION
Reference 1 has pointed necessity of including the acceleration derivatives Cn.β and CZ.β as determined from oscillation tests in calculations of dynamic lateral stability. This is especially true at the high angles of attack since references 2 and–3 show that rather large values of the acceleration derivatives may occur for certain configurations under these conditions. Since a 60° delta wing showed high values of oscillatory yawing derivatives at high angles of attack (refs. 2 and 3), information concerning the oscillatory yawing derivatives of narrow delta wings, which might be used in missile configurations, was thought to be of interest. The present investigation was undertaken, therefore, to provide some information regarding the effects of frequency and amplitude on narrow delta wings oscillating in yaw at angles of attack from 0° to the angle of maximum lift.
The present investigation consisted of determining the effects of a systematic variation of frequency and amplitude of oscillation on the oscillatory derivatives of 82.5° and 75° delta wings. Static stability for these and for 86.5°, 60°, 45°, and 30° delta wings was also determined. Oscillatory derivatives for a 60° delta wing from reference 3 are also presented for comparison purposes. The oscillatory derivatives from reference 3 and those obtained in the present investigation were obtained by a forced oscillation technique; the motion was a combination of yawing and sideslipping and provided the combination derivatives.
Reference 1 has pointed necessity of including the acceleration derivatives Cn.β and CZ.β as determined from oscillation tests in calculations of dynamic lateral stability. This is especially true at the high angles of attack since references 2 and–3 show that rather large values of the acceleration derivatives may occur for certain configurations under these conditions. Since a 60° delta wing showed high values of oscillatory yawing derivatives at high angles of attack (refs. 2 and 3), information concerning the oscillatory yawing derivatives of narrow delta wings, which might be used in missile configurations, was thought to be of interest. The present investigation was undertaken, therefore, to provide some information regarding the effects of frequency and amplitude on narrow delta wings oscillating in yaw at angles of attack from 0° to the angle of maximum lift.
The present investigation consisted of determining the effects of a systematic variation of frequency and amplitude of oscillation on the oscillatory derivatives of 82.5° and 75° delta wings. Static stability for these and for 86.5°, 60°, 45°, and 30° delta wings was also determined. Oscillatory derivatives for a 60° delta wing from reference 3 are also presented for comparison purposes. The oscillatory derivatives from reference 3 and those obtained in the present investigation were obtained by a forced oscillation technique; the motion was a combination of yawing and sideslipping and provided the combination derivatives.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:42:54Z | |
| date available | 2017-09-04T17:42:54Z | |
| date copyright | 01/01/1957 | |
| date issued | 1957 | |
| identifier other | EBYIYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/165928 | |
| description abstract | INTRODUCTION Reference 1 has pointed necessity of including the acceleration derivatives Cn.β and CZ.β as determined from oscillation tests in calculations of dynamic lateral stability. This is especially true at the high angles of attack since references 2 and–3 show that rather large values of the acceleration derivatives may occur for certain configurations under these conditions. Since a 60° delta wing showed high values of oscillatory yawing derivatives at high angles of attack (refs. 2 and 3), information concerning the oscillatory yawing derivatives of narrow delta wings, which might be used in missile configurations, was thought to be of interest. The present investigation was undertaken, therefore, to provide some information regarding the effects of frequency and amplitude on narrow delta wings oscillating in yaw at angles of attack from 0° to the angle of maximum lift. The present investigation consisted of determining the effects of a systematic variation of frequency and amplitude of oscillation on the oscillatory derivatives of 82.5° and 75° delta wings. Static stability for these and for 86.5°, 60°, 45°, and 30° delta wings was also determined. Oscillatory derivatives for a 60° delta wing from reference 3 are also presented for comparison purposes. The oscillatory derivatives from reference 3 and those obtained in the present investigation were obtained by a forced oscillation technique; the motion was a combination of yawing and sideslipping and provided the combination derivatives. | |
| language | English | |
| title | NACA-RM-L57A30 | num |
| title | Experimental determination at subsonic speeds of the oscillatory and static lateral stability derivatives of a series of delta wings with leading-edge sweep from 30 degrees to 86.5 degrees | en |
| type | standard | |
| page | 39 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1957 | |
| contenttype | fulltext |