درباره ما
NACA-RM-L52E02
Longitudinal frequency-response and stability characteristics of the Douglas D-558-II airplane as determined from transient response to a Mach number of 0.96
Year: 1952
Abstract: INTRODUCTION
An investigation is currently being conducted by the National Advisory Committee for Aeronautics to determine the dynamic response characteristics of research airplanes through the transonic speed range. As a part of this investigation, some results on the dynamic longitudinal response characteristics of the Douglas D-558-II research airplane have been obtained. These data are somewhat complete below a Mach number of 0.85 for two altitude ranges. Some data are presented for higher test Mach numbers and altitudes because of the general interest in data of this type.
Of the several methods of obtaining the frequency response of freeflight dynamical systems, the pulse-disturbance technique was used because a minimum of flight time and instrumentation is required. Also, no special device is necessary to actuate the input control. By a Fourier analysis of the airplane response to an elevator- pulse, the frequency response of the airplane has been obtained. These results have been reduced to airplane stability derivatives.
These tests were conducted over a Mach number range of 0.60 to 0.96 at altitudes ranging from 21,000 to 43,000 feet. For purposes of analysis the data have been divided into three altitude ranges: 21,000 to 25,000 feet, 28,000 to 33,000 feet, and at 37,500 and 43,000 feet.
An investigation is currently being conducted by the National Advisory Committee for Aeronautics to determine the dynamic response characteristics of research airplanes through the transonic speed range. As a part of this investigation, some results on the dynamic longitudinal response characteristics of the Douglas D-558-II research airplane have been obtained. These data are somewhat complete below a Mach number of 0.85 for two altitude ranges. Some data are presented for higher test Mach numbers and altitudes because of the general interest in data of this type.
Of the several methods of obtaining the frequency response of freeflight dynamical systems, the pulse-disturbance technique was used because a minimum of flight time and instrumentation is required. Also, no special device is necessary to actuate the input control. By a Fourier analysis of the airplane response to an elevator- pulse, the frequency response of the airplane has been obtained. These results have been reduced to airplane stability derivatives.
These tests were conducted over a Mach number range of 0.60 to 0.96 at altitudes ranging from 21,000 to 43,000 feet. For purposes of analysis the data have been divided into three altitude ranges: 21,000 to 25,000 feet, 28,000 to 33,000 feet, and at 37,500 and 43,000 feet.
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:06:36Z | |
| date available | 2017-09-04T18:06:36Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | GMSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/189520 | |
| description abstract | INTRODUCTION An investigation is currently being conducted by the National Advisory Committee for Aeronautics to determine the dynamic response characteristics of research airplanes through the transonic speed range. As a part of this investigation, some results on the dynamic longitudinal response characteristics of the Douglas D-558-II research airplane have been obtained. These data are somewhat complete below a Mach number of 0.85 for two altitude ranges. Some data are presented for higher test Mach numbers and altitudes because of the general interest in data of this type. Of the several methods of obtaining the frequency response of freeflight dynamical systems, the pulse-disturbance technique was used because a minimum of flight time and instrumentation is required. Also, no special device is necessary to actuate the input control. By a Fourier analysis of the airplane response to an elevator- pulse, the frequency response of the airplane has been obtained. These results have been reduced to airplane stability derivatives. These tests were conducted over a Mach number range of 0.60 to 0.96 at altitudes ranging from 21,000 to 43,000 feet. For purposes of analysis the data have been divided into three altitude ranges: 21,000 to 25,000 feet, 28,000 to 33,000 feet, and at 37,500 and 43,000 feet. | |
| language | English | |
| title | NACA-RM-L52E02 | num |
| title | Longitudinal frequency-response and stability characteristics of the Douglas D-558-II airplane as determined from transient response to a Mach number of 0.96 | en |
| type | standard | |
| page | 37 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |