درباره ما
NACA-RM-A50J09 REV A
Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane
Year: 1950
Abstract: INTRODUCTION
At the present time there are only limited data available on the dynamic behavior of swept-wing aircraft, especially at transonic speeds. The flight-test program being conducted by the NACA on a 35° swept-wing airplane includes the determination of dynamic directional-, lateral-, and longitudinal-stability characteristics as affected by Mach number.
This report presents the preliminary results of a flight investigation into the longitudinal-stability characteristics of the test airplane. The simple method of analysis used here is possible because the airplane exhibits a lightly damped short period oscillatory response. The computed flight-test characteristics are compared with estimations made from static wind-tunnel data.
More complete analyses, using additional flight data, are being carried out in order to determine the frequency responses of the airplane and the individual stability derivatives through the subsonic and transonic speed ranges.
At the present time there are only limited data available on the dynamic behavior of swept-wing aircraft, especially at transonic speeds. The flight-test program being conducted by the NACA on a 35° swept-wing airplane includes the determination of dynamic directional-, lateral-, and longitudinal-stability characteristics as affected by Mach number.
This report presents the preliminary results of a flight investigation into the longitudinal-stability characteristics of the test airplane. The simple method of analysis used here is possible because the airplane exhibits a lightly damped short period oscillatory response. The computed flight-test characteristics are compared with estimations made from static wind-tunnel data.
More complete analyses, using additional flight data, are being carried out in order to determine the frequency responses of the airplane and the individual stability derivatives through the subsonic and transonic speed ranges.
-
Statistics
NACA-RM-A50J09 REV A
Show full item record
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:45:04Z | |
| date available | 2017-09-04T15:45:04Z | |
| date copyright | 01/01/1950 | |
| date issued | 1950 | |
| identifier other | PRCTUDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/47553 | |
| description abstract | INTRODUCTION At the present time there are only limited data available on the dynamic behavior of swept-wing aircraft, especially at transonic speeds. The flight-test program being conducted by the NACA on a 35° swept-wing airplane includes the determination of dynamic directional-, lateral-, and longitudinal-stability characteristics as affected by Mach number. This report presents the preliminary results of a flight investigation into the longitudinal-stability characteristics of the test airplane. The simple method of analysis used here is possible because the airplane exhibits a lightly damped short period oscillatory response. The computed flight-test characteristics are compared with estimations made from static wind-tunnel data. More complete analyses, using additional flight data, are being carried out in order to determine the frequency responses of the airplane and the individual stability derivatives through the subsonic and transonic speed ranges. | |
| language | English | |
| title | NACA-RM-A50J09 REV A | num |
| title | Preliminary flight investigation of the dynamic longitudinal-stability characteristics of a 35 degree swept-wing airplane | en |
| type | standard | |
| page | 28 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1950 | |
| contenttype | fulltext |