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NASA-TM-X-3078
Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage
Year: 1974
Abstract: An investigation has been made in the Mach number range from 0.20 to 2.16 to determine the longitudinal aerodynamic characteristics of a fighter airplane concept. The configuration concept employs a single fixed geometry inlet, a 50 deg leading-edge-angle clipped-arrow wing, a single large vertical tail, and low horizontal tails. The wing camber surface was optimized in drag due to lift and was designed to be self-trimming at Mach 1.40 and at a lift coefficient of 0.20. An uncambered or flat wing of the same planform and thickness ratio was also tested. However, for the present investigation, the fuselage was not cambered. Further tests should be made on a cambered fuselage version, which attempts to preserve the optimum wing loading on that part of the theoretical wing enclosed by the fuselage.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T16:37:04Z | |
| date available | 2017-09-04T16:37:04Z | |
| date copyright | 01/01/1974 | |
| date issued | 1974 | |
| identifier other | VENKAEAAAAAAAAAA.pdf | |
| identifier uri | https://yse.yabesh.ir/std/handle/yse/100588 | |
| description abstract | An investigation has been made in the Mach number range from 0.20 to 2.16 to determine the longitudinal aerodynamic characteristics of a fighter airplane concept. The configuration concept employs a single fixed geometry inlet, a 50 deg leading-edge-angle clipped-arrow wing, a single large vertical tail, and low horizontal tails. The wing camber surface was optimized in drag due to lift and was designed to be self-trimming at Mach 1.40 and at a lift coefficient of 0.20. An uncambered or flat wing of the same planform and thickness ratio was also tested. However, for the present investigation, the fuselage was not cambered. Further tests should be made on a cambered fuselage version, which attempts to preserve the optimum wing loading on that part of the theoretical wing enclosed by the fuselage. | |
| language | English | |
| title | NASA-TM-X-3078 | num |
| title | Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage | en |
| type | standard | |
| page | 99 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1974 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | AIRCRAFT | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | CONFIGURATIONS | |
| subject keywords | CONTROL | |
| subject keywords | FIGHTER | |
| subject keywords | FLIGHT | |
| subject keywords | LONGITUDINAL | |
| subject keywords | PERFORMANCE | |
| subject keywords | PREDICTION | |
| subject keywords | STABILITY | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND |