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NASA-TM-X-3437
Side forces on a tangent ogive forebody with a fineness ratio of 3.5 at high angles of attack and Mach numbers from 0.1 to 0.7
Year: 1977
Abstract: An experimental investigation was conducted in the Ames 12-Foot Wind Tunnel to determine the subsonic aerodynamic characteristics, at high angles of attack, of a tangent ogive forebody with a fineness ratio of 3.5. The investigation included the effects of nose bluntness, nose strakes, nose booms, a simulated canopy, and boundary-layer trips. The forebody was also tested with a short afterbody attached. Static longitudinal and lateral-directional stability data were obtained at Reynolds numbers ranging from 0.3 mil. to 3.8 mil. (based on base diameter) at a Mach number of 0.25, and at a Reynolds number of 0.8 mil. at Mach numbers ranging from 0.1 to 0.7. Angle of attack was varied from 0 to 88 deg at zero sideslip, and the sideslip angle was varied from -10 to 30 deg at angles of attack of 40, 55, and 70 deg.
Subject: AERODYNAMIC
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T17:30:51Z | |
| date available | 2017-09-04T17:30:51Z | |
| date copyright | 01/01/1977 | |
| date issued | 1977 | |
| identifier other | CVTKAEAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std/handle/yse/153763 | |
| description abstract | An experimental investigation was conducted in the Ames 12-Foot Wind Tunnel to determine the subsonic aerodynamic characteristics, at high angles of attack, of a tangent ogive forebody with a fineness ratio of 3.5. The investigation included the effects of nose bluntness, nose strakes, nose booms, a simulated canopy, and boundary-layer trips. The forebody was also tested with a short afterbody attached. Static longitudinal and lateral-directional stability data were obtained at Reynolds numbers ranging from 0.3 mil. to 3.8 mil. (based on base diameter) at a Mach number of 0.25, and at a Reynolds number of 0.8 mil. at Mach numbers ranging from 0.1 to 0.7. Angle of attack was varied from 0 to 88 deg at zero sideslip, and the sideslip angle was varied from -10 to 30 deg at angles of attack of 40, 55, and 70 deg. | |
| language | English | |
| title | NASA-TM-X-3437 | num |
| title | Side forces on a tangent ogive forebody with a fineness ratio of 3.5 at high angles of attack and Mach numbers from 0.1 to 0.7 | en |
| type | standard | |
| page | 115 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1977 | |
| contenttype | fulltext | |
| subject keywords | AERODYNAMIC | |
| subject keywords | ANGLE | |
| subject keywords | ATTACK | |
| subject keywords | BODIES | |
| subject keywords | CHARACTERISTICS | |
| subject keywords | FORCES | |
| subject keywords | FOREBODIES | |
| subject keywords | MACH | |
| subject keywords | NUMBER | |
| subject keywords | OGIVES | |
| subject keywords | REVOLUTION | |
| subject keywords | REYNOLDS | |
| subject keywords | SIDESLIP | |
| subject keywords | TESTS | |
| subject keywords | TUNNEL | |
| subject keywords | WIND | |
| subject keywords | YAW |