Dynamic Finite Element Analysis of the Sting of the CF-18 Wind Tunnel Model at 120 Angle of Attack PDF Download
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Category :
Languages : en
Pages : 3
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Author:
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Category :
Languages : en
Pages : 3
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Category :
Languages : en
Pages : 5
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Author: James P. Billingsley
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Category : Aerodynamic load
Languages : en
Pages : 64
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Wind tunnel model support stings can be subjected to transient aerodynamic and inertial loads which will create oscillatory translations and angular deflections. These transient oscillations always impair steady-state data accuracy and can be large enough to cause structural failure. The primary result of this investigation has been the formulation of a mathematical analysis for the dynamic response of sting-balance combinations subjected to arbitrary transient load inputs. The analysis also provides for sting rigid body motion so that model to tunnel injection and continuous sting rotation can be simulated. A computer program was written to numerically solve the sting-model-balance notion equations.
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Languages : en
Pages : 0
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Wind tunnel model support stings can be subjected to transient aerodynamic and inertial loads which will create oscillatory translations and angular deflections. These transient oscillations always impair steady-state data accuracy and can be large enough to cause structural failure. The primary result of this investigation has been the formulation of a mathematical analysis for the dynamic response of sting-balance combinations subjected to arbitrary transient load inputs. The analysis also provides for sting rigid body motion so that model to tunnel injection and continuous sting rotation can be simulated. A computer program was written to numerically solve the sting-model-balance notion equations.
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Category :
Languages : en
Pages : 0
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Wind tunnel model support stings can be subjected to transient aerodynamic and inertial loads which will create oscillatory translations and angular deflections. These transient oscillations always impair steady-state data accuracy and can be large enough to cause structural failure. The primary result of this investigation has been the formulation of a mathematical analysis for the dynamic response of sting-balance combinations subjected to arbitrary transient load inputs. The analysis also provides for sting rigid body motion so that model to tunnel injection and continuous sting rotation can be simulated. A computer program was written to numerically solve the sting-model-balance notion equations.
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ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 620
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Author: B. J. Griffith
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Category : Aerodynamics
Languages : en
Pages : 32
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High Mach number wind tunnel drag, lift, moment, and heat-transfer data from sting-mounted models are compared, with available free-flight data. The resulting comparisons show that there is an apparent lack of support interference effects on forebody flow fields of slender cones, and that the so-called real gas effects on the observed data are insignificant at velocities up to 18,000 ft/sec.
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Category : Aeronautics
Languages : en
Pages : 1460
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Book Description
Lists citations with abstracts for aerospace related reports obtained from world wide sources and announces documents that have recently been entered into the NASA Scientific and Technical Information Database.
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Languages : en
Pages : 20
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Author: In Lee
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Category :
Languages : en
Pages : 140
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