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Experimental study of tail-span effects on a generic canard-controlled missileAn experimental investigation was conducted on a cruciform canard controlled missile configuration to determine the effects of tail span/canard span ratio on controllability. The investigation was conducted over the Mach number range of 1.75 to 3.50. Reductions of tail span/canard span ratio produced lower static margins and higher trim angle of attack. The results show that canard controls can provide pitch- and yaw-control as well as roll-control by proper selection of the tail span/canard span ratio.
Document ID
19920039566
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Blair, A. B., Jr.
(NASA Langley Research Center Hampton, VA, United States)
Dillon, James L.
(NASA Langley Research Center Hampton, VA, United States)
Watson, Carolyn B.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1992
Subject Category
Aircraft Stability And Control
Report/Patent Number
AIAA PAPER 92-0079
Accession Number
92A22190
Distribution Limits
Public
Copyright
Other

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