درباره ما
NACA-RM-L56D16 REV A
The Effects of the Addition of Small Fuselage-Mounted Fins on the Static Directional Stability Characteristics of a Model of a 45 Degrees Swept-Wing Airplane at Angles of Attack up to 15.3 degrees at a Mach Number of 2.01
| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T15:19:35Z | |
| date available | 2017-09-04T15:19:35Z | |
| date copyright | 01/01/1956 | |
| date issued | 1956 | |
| identifier other | ASSWXDAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/19423 | |
| description abstract | Tests have been made in the Langley 4- by 4-foot supersonic pressure tunnel at a Mach number of 2.01 to determine the effects of the addition of four small fuselage-mounted cruciform fins on the directional characteristics of a 45 deg swept-wing airplane model at angles of attack up to 15.3 deg and angles of sideslip up to about 16 deg. The results showed that the addition of the four cruciform fins to the model increased the directional stability substantially at the highest angle of attack and, at the same time, caused relatively small changes in drag. | |
| language | English | |
| title | NACA-RM-L56D16 REV A | num |
| title | The Effects of the Addition of Small Fuselage-Mounted Fins on the Static Directional Stability Characteristics of a Model of a 45 Degrees Swept-Wing Airplane at Angles of Attack up to 15.3 degrees at a Mach Number of 2.01 | en |
| type | standard | |
| page | 27 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1956 | |
| contenttype | fulltext |
