| タイトル | Experimental investigation of a new device to control the asymmetric flowfield on forebodies at large angles of attack |
| 著者（英） | Hall, Robert M.; Moskovitz, Cary A.; Dejarnette, F. R. |
| 著者所属（英） | Virginia Polytechnic Inst. and State Univ.; North Carolina State Univ.; NASA Langley Research Center |
| 発行日 | 1990-01-01 |
| 言語 | eng |
| 内容記述 | An exploratory experimental investigation of a new device to control the asymmetric flowfield on forebodies at large angles of attack has been conducted. The device is a rotatable forebody tip, which varies in cross section from circular at its base to elliptic at its tip. The device itself extends over a small portion of the aircraft or missile forebody. The device provides two important improvements. First, it replaced the normally random behavior of the nose side force as a function of nose tip orientation with a predictable and generally sinusoidal distribution and, second, the device showed promise for use as part of a vehicle control system, to be deflected in a prescribed manner to provide additional directional control for the vehicle. The device was tested on a cone/cylinder model having a 10 deg semiapex angle and on a 3.0 caliber tangent ogive model, each with a base diameter of 3.5 in, for angles of attack from 30 to 60 deg. Data were taken from 3 circumferential rows of pressure taps on each model at a Reynolds number of 84,000 based on cylinder diameter and by a helium-bubble flow visualization technique at a Reynolds number of 24,000. |
| NASA分類 | AERODYNAMICS |
| レポートNO | 90A19665
AIAA PAPER 90-0069 |
| 権利 | Copyright |
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