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NASA-TN-D-6909
Dynamic stability derivatives at angles of attack from -5 degrees to 90 degrees for a variable-sweep fighter configuration with twin vertical tails
Year: 1972
Abstract: An investigation was conducted in the Langley full-scale tunnel to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails. The study consisted of forced-oscillation tests of a 1/10-scale model of the airplane at a Reynolds number of 0.4 million based on the reference wing mean aerodynamic chord. Tests were conducted for wing sweep angles of 22 deg, 35 deg, 50 deg, and 68 deg, and the effects of the vertical and horizontal tails, wing leading-edge slats, nose-mounted canards, and frequency of the oscillation were also evaluated.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:47:01Z | |
| date available | 2017-09-04T18:47:01Z | |
| date copyright | 01/01/1972 | |
| date issued | 1972 | |
| identifier other | AMYKAEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;query=authoCA58ear3081D206861598F1EFDEC014A/handle/yse/228217 | |
| description abstract | An investigation was conducted in the Langley full-scale tunnel to determine the dynamic stability derivatives in pitch, roll, and yaw over an angle-of-attack range of -5 deg to 90 deg for a variable-sweep fighter configuration with twin vertical tails. The study consisted of forced-oscillation tests of a 1/10-scale model of the airplane at a Reynolds number of 0.4 million based on the reference wing mean aerodynamic chord. Tests were conducted for wing sweep angles of 22 deg, 35 deg, 50 deg, and 68 deg, and the effects of the vertical and horizontal tails, wing leading-edge slats, nose-mounted canards, and frequency of the oscillation were also evaluated. | |
| language | English | |
| title | NASA-TN-D-6909 | num |
| title | Dynamic stability derivatives at angles of attack from -5 degrees to 90 degrees for a variable-sweep fighter configuration with twin vertical tails | en |
| type | standard | |
| page | 54 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1972 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRCRAFT | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | CONFIGURATIONS | |
| subject keywords | DERIVATIVES | |
| subject keywords | FIGHTER | |
| subject keywords | STABILITY | |
| subject keywords | SWEEP | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | VARIABLE | |
| subject keywords | WIND | |
| subject keywords | WINGS |