Kanagarajan, V and Arokkiaswamy, A (1986) Some studies on induced rolling moment of a missile type configuration 13; 13;. In: 2nd National Conference on Aerodynamics, 19-20 Dec 1986, Bangalore, India.Full text not available from this repository.
Force tests were carried out on a typical missile configuration, featuring a slender body cruciform canard and cruciform tail, in a 1.2-m wind tunnel at subsonic, transonic, and supersonic speeds at various incidence and control deflections. Some discussions on the induced rolling moment experienced by this configuration during maneuvering attitudes are presented. It was observed that the induced rolling moment was primarily due to the interaction of asymmetric flow field induced by the canard deflections on the tail. This induced rolling moment was negligibly small when the tail fins were removed. Also, the variation of the induced rolling moment with incidence was approximately sinusoidal for most of the canard deflections. This paper also includes some discussions on a current method adopted for eliminating such undesirable induced rolling moments by allowing the tail fin to roll freely.
|Item Type:||Conference or Workshop Item (Paper)|
|Uncontrolled Keywords:||Rolling;Moments;Deflection;Aeronautics;Cruciform tests; Missiles;Variations;Rolls;Aerodynamics;Organizations; Asymmetry;Wind tunnels;Fins;Supersonic aircraft|
|Subjects:||AERONAUTICS > Aeronautics (General)|
|Depositing User:||M/S ICAST NAL|
|Date Deposited:||12 Oct 2006|
|Last Modified:||24 May 2010 09:51|
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