Yaw Control at High Angles of Attack Through Vortex Manipulation Using Rotating Nose Strakes
DAIMLER CHRYSLER AEROSPACE AG MUENCHEN (GERMANY) MILITARY AIRCRAFT DIV
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The effect of nose strakes on the flow field in the vicinity of the forward fuselage section of an aircraft was investigated. Emphasis was placed on the manipulation of the vortices in order to generate a significant side force and yawing moment with the purpose not only to stabilize the aircraft at high angles of incidence but also to achieve yaw control. Aside from conventional control surfaces an additional control device was realized by mounting a single strake on the nose section which could be rotated around its longitudinal axis. Experimental force and pressure data from low speed wind tunnel tests indicate the potential of this control device for aircraft flying at high angles of attack.
- Attack and Fighter Aircraft