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Experimental and Analytical Investigation of the Transonic and Supersonic Divergence Characteristics of a Delta-Plan-Form All- Movable ControlThe static aeroelastic divergence characteristics of a delta-planform model of the canard control surface of a proposed air-to-ground missile have been studied both analytically and experimentally in the Mach number range from 0.6 to 3.0. The experiments indicated that divergence occurred at a nearly constant value of dynamic pressure at Mach numbers up to 1.2. At higher Mach numbers somewhat higher values of dynamic pressure were required to produce divergence. The analysis and the experiment indicate that the camber stiffness of the control surface and the stiffness of the control actuator are both important in divergence of surfaces of this type.
Document ID
19650013735
Acquisition Source
Legacy CDMS
Document Type
Other - NACA Research Memorandum
Authors
Rainey, A. G. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Hanson, P. W. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Martin, D. J. (National Advisory Committee for Aeronautics. Langley Aeronautical Lab. Langley Field, VA, United States)
Date Acquired
August 2, 2013
Publication Date
August 4, 1958
Subject Category
Aerodynamics
Report/Patent Number
NACA-RM-L58E07
Accession Number
65N23336
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
Keywords
PLANFORM
CONTROL SURFACE
AEROELASTICITY
AIR TO SURFACE MISSILE

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