Accession Number : AD0448910


Title :   SOME STATIC AEROELASTIC CONSIDERATIONS OF SLENDER AIRCRAFT


Corporate Author : ADVISORY GROUP FOR AERONAUTICAL RESEARCH AND DEVELOPMENT PARIS (FRANCE)


Personal Author(s) : Hancock, G J


Full Text : https://apps.dtic.mil/dtic/tr/fulltext/u2/448910.pdf


Report Date : Apr 1961


Pagination or Media Count : 33


Abstract : A series of simple theoretical models are discussed, representing the essential features of flexible aircraft both of the classical and integrated varieties, in trimmed level flight. Assuming linear aerodynamics it is shown that the maximum speed for trimmed flight for the classical aircraft is determined primarily by the tail-plane flexibility. For the integrated aircraft this maximum speed occurs when both the overall aeroelastic distortion and the control forces become very large, the effectiveness of the control to trim is related to the similarity of the weight and aerodynamic lifting distributions. Detailed calculations on trimmed plate wings of varying plan form further illustrate these general points. The aeroelastic effect of these trimmed plate wings in level flight are also investigated assuming non-linear aerodynamics. It is shown that in general there are two positions of equilibrium of the aircraft at each speed although it is possible that at high speeds both these positions of equilibrium are imaginary. The stability of these positions of equilibrium are not discussed in this paper.


Descriptors :   *SUPERSONIC AIRCRAFT , SUPERSONIC AIRFOILS , SLENDER BODIES , BEAMS(STRUCTURAL) , DEFLECTION , AEROELASTICITY , MATHEMATICAL ANALYSIS , AERODYNAMIC LOADING , FUSELAGES , LEVEL FLIGHT , WINGS , DELTA WINGS , FLEXIBLE STRUCTURES , TAILS(AIRCRAFT) , MATHEMATICAL MODELS , SIMULATION


Subject Categories : Aircraft


Distribution Statement : APPROVED FOR PUBLIC RELEASE