DTIC AD0448909: THE INFLUENCE OF AEROELASTICITY ON pdf

DTIC AD0448909: THE INFLUENCE OF AEROELASTICITY ON

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A numerical treatment of the influence of the aeroelastic deformations on the longitudinal stability and control characteristics of an aircraft with a swept-back wing of large aspect ratio is carried out for the sub-critical speed range. Only the deformation of the wing and the bending of the fuselage have been taken into consideration. The method used to calculate the deformations of the wing is based on the superposition of a number of pre- selected load distributions (A Superposition Method for Calculating the Aeroelastic Behavior of Swept Wings, Aug. 1951, by R. B. Brown et alii). An investigation of the accuracy of the method has been made by comparing the numerical results with those of another more exact method which proved the reliability of the present method. As a result of the study it was found that the stability and control of the aircraft are only slightly affected by the aeroelastic deformation

• Creator/s: Defense Technical Information Center
• Date: 4/1/1961
• Year: 1961
• Book Topics/Themes: DTIC Archive, Kalkman, C M, ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE), *JET TRANSPORT AIRCRAFT, TAILS(AIRCRAFT), DEFORMATION, DEFLECTION, ANGLE OF ATTACK, AEROELASTICITY, AERODYNAMIC LOADING, FUSELAGES, SUBSONIC CHARACTERISTICS, LIFT, DOWNWASH, ASPECT RATIO, SWEPTBACK WINGS, STABILITY, PITCH(MOTION

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