| タイトル | Aerodynamic Characteristics of Towed Cones Used as Decelerators at Mach Numbers from 1.57 to 4.65 |
| 本文（外部サイト） | http://hdl.handle.net/2060/19980228057 |
| 著者（英） | McShera, John T.; Charczenko, Nickolai |
| 著者所属（英） | NASA Langley Research Center |
| 発行日 | 1961-12-01 |
| 言語 | eng |
| 内容記述 | Towed and sting-supported cones were tested in the wake of various payloads at supersonic speeds to determine their drag and stability characteristics. The investigation extended over a Mach number range from 1.57 to 4.65 and included such variables as Reynolds number, cone angle, ratio of cone base diameter to payload base diameter, and trailing distance. The results of this investigation showed that the cones towed in the wake of a symmetrical payload at supersonic speeds, in general, have good drag and stability characteristics if towed in the supersonic flow region. A cone with an included angle between 80 deg and 90 deg will give maximum drag while still maintaining stability in the Mach number region of this investigation. In order to minimize wake effects, the ratio of cone base diameter to payload base diameter should be at least one and preferably around three. A trailing distance of three times the payload base diameter, in most cases, is of sufficient length to avoid low drag and instability of the decelerator. |
| NASA分類 | Aerodynamics |
| レポートNO | NASA-TN-D-994
L-1505 |
| 権利 | No Copyright |
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