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NACA-TN-1080
Summary and analysis of data on damping in yaw and pitch for a numbers of airplane models
Year: 1946
Abstract: INTRODUCTION
Dynamic-stability calculations for an airplane require knowledge of values of the damping-in pitch derivative cmq (the pitching-moment coefficient due to pitching velocity) and the damping-in-yaw parameter cnr ( the yawing-moment coefficient due to yawing velocity). At the present time, however, very little experimental data on these derivatives for modern airplanes are available.
The damping derivatives cmq and cnr have been measured in the Langley free-flight tunnel during stability investigations as an aid in analyzing the stability characteristics of some models. These measurements are summarized herein to provide a source of experimental data, and a limited analysis of the data and a comparison with calculated results are also presented. The values of cnr and cmq were determined experimentally by the free-oscillation method described in reference 1 and 2. The calculations were made by the methods of references 2 to 6
Data are presented for a rectangular wing and for 13 complete airplane models, five of which are tailless designs. The term "tailless" refers to an airplane with no horizontal tail; however, such designs generally incorporate some type of vertical tail. The term "conventional" in this paper refers to airplanes other than tailless airplanes. Values of cnr and cmq over the normal lift range are presented in most cases. The effects of tail area, tail length, flap deflection, and power on the damping in yaw and pitch are shown.
Dynamic-stability calculations for an airplane require knowledge of values of the damping-in pitch derivative cmq (the pitching-moment coefficient due to pitching velocity) and the damping-in-yaw parameter cnr ( the yawing-moment coefficient due to yawing velocity). At the present time, however, very little experimental data on these derivatives for modern airplanes are available.
The damping derivatives cmq and cnr have been measured in the Langley free-flight tunnel during stability investigations as an aid in analyzing the stability characteristics of some models. These measurements are summarized herein to provide a source of experimental data, and a limited analysis of the data and a comparison with calculated results are also presented. The values of cnr and cmq were determined experimentally by the free-oscillation method described in reference 1 and 2. The calculations were made by the methods of references 2 to 6
Data are presented for a rectangular wing and for 13 complete airplane models, five of which are tailless designs. The term "tailless" refers to an airplane with no horizontal tail; however, such designs generally incorporate some type of vertical tail. The term "conventional" in this paper refers to airplanes other than tailless airplanes. Values of cnr and cmq over the normal lift range are presented in most cases. The effects of tail area, tail length, flap deflection, and power on the damping in yaw and pitch are shown.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:15:44Z | |
| date available | 2017-09-04T18:15:44Z | |
| date copyright | 01/01/1946 | |
| date issued | 1946 | |
| identifier other | HKYIYDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/198605 | |
| description abstract | INTRODUCTION Dynamic-stability calculations for an airplane require knowledge of values of the damping-in pitch derivative cmq (the pitching-moment coefficient due to pitching velocity) and the damping-in-yaw parameter cnr ( the yawing-moment coefficient due to yawing velocity). At the present time, however, very little experimental data on these derivatives for modern airplanes are available. The damping derivatives cmq and cnr have been measured in the Langley free-flight tunnel during stability investigations as an aid in analyzing the stability characteristics of some models. These measurements are summarized herein to provide a source of experimental data, and a limited analysis of the data and a comparison with calculated results are also presented. The values of cnr and cmq were determined experimentally by the free-oscillation method described in reference 1 and 2. The calculations were made by the methods of references 2 to 6 Data are presented for a rectangular wing and for 13 complete airplane models, five of which are tailless designs. The term "tailless" refers to an airplane with no horizontal tail; however, such designs generally incorporate some type of vertical tail. The term "conventional" in this paper refers to airplanes other than tailless airplanes. Values of cnr and cmq over the normal lift range are presented in most cases. The effects of tail area, tail length, flap deflection, and power on the damping in yaw and pitch are shown. | |
| language | English | |
| title | NACA-TN-1080 | num |
| title | Summary and analysis of data on damping in yaw and pitch for a numbers of airplane models | en |
| type | standard | |
| page | 48 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1946 | |
| contenttype | fulltext |