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NACA-RM-L52G07
Wind-tunnel investigation of the low-speed static and rotary stability derivatives of a 0.13-scale model of the Douglas D-558-II airplane in the landing configuration
Year: 1952
Abstract: INTRODUCTION
Various investigations have shown that the dynamic lateral stability characteristics of high-speed aircraft are critically dependent on certain mass and aerodynamic parameters and, hence, that reliable estimates of the dynamic stability of such aircraft can be made only if these parameters are determined accurately. The static derivatives of an airplane can be determined accurately by means of conventional wind-tunnel tests of a model; however, only a few facilities are available for measuring rotary (rolling and yawing) derivatives. The Langley stability tunnel, which is equipped with facilities for simulating rolling and yawing flaw, was utilized to make available measured low-speed static and rotary derivatives of a model of the Douglas D-558-II airplane in the landing configuration (slats, flaps, and landing gear extended). The measured low-speed parameters of the same model with slats, flaps, and landing gear retracted are given in reference 1.
Various investigations have shown that the dynamic lateral stability characteristics of high-speed aircraft are critically dependent on certain mass and aerodynamic parameters and, hence, that reliable estimates of the dynamic stability of such aircraft can be made only if these parameters are determined accurately. The static derivatives of an airplane can be determined accurately by means of conventional wind-tunnel tests of a model; however, only a few facilities are available for measuring rotary (rolling and yawing) derivatives. The Langley stability tunnel, which is equipped with facilities for simulating rolling and yawing flaw, was utilized to make available measured low-speed static and rotary derivatives of a model of the Douglas D-558-II airplane in the landing configuration (slats, flaps, and landing gear extended). The measured low-speed parameters of the same model with slats, flaps, and landing gear retracted are given in reference 1.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:17:22Z | |
| date available | 2017-09-04T15:17:22Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | MMSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/16793 | |
| description abstract | INTRODUCTION Various investigations have shown that the dynamic lateral stability characteristics of high-speed aircraft are critically dependent on certain mass and aerodynamic parameters and, hence, that reliable estimates of the dynamic stability of such aircraft can be made only if these parameters are determined accurately. The static derivatives of an airplane can be determined accurately by means of conventional wind-tunnel tests of a model; however, only a few facilities are available for measuring rotary (rolling and yawing) derivatives. The Langley stability tunnel, which is equipped with facilities for simulating rolling and yawing flaw, was utilized to make available measured low-speed static and rotary derivatives of a model of the Douglas D-558-II airplane in the landing configuration (slats, flaps, and landing gear extended). The measured low-speed parameters of the same model with slats, flaps, and landing gear retracted are given in reference 1. | |
| language | English | |
| title | NACA-RM-L52G07 | num |
| title | Wind-tunnel investigation of the low-speed static and rotary stability derivatives of a 0.13-scale model of the Douglas D-558-II airplane in the landing configuration | en |
| type | standard | |
| page | 19 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |