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NASA Technical Note
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Flutter Analysis of Rectangular Wings of Very Low Aspect Ratio
A flutter analysis, employing slender-body aerodynamic theory and thin-plate theory, is made for rectangular wings of very low aspect ratio with a constant thickness. The spanwise variation of wing deflection is assumed to be given by a parabola, and the chordwise variation is allowed complete freedom. The results show the vsriation of flutter speed and male shape with aspect ratio. Comparisons are made with additional resuits obtained by approximating the chordwise deflection shape by use of parabolic or cubic curves. The analysis shows that the cubic approximation gives good resuits for a ratio of chord to semispan less than 3.
Coupling Dynamics in Aircraft
Presents archival anecdotes and analyses of coupling problems experienced by the X-series, Century series, and Space Shuttle aircraft. The three catastrophic sequential coupling modes of the X-2 airplane and the two simultaneous unstable modes of the X-15 and Space Shuttle aircraft are discussed. In addition, the most complex of the coupling interactions, inertia roll coupling, is discussed for the X-2, X-3, F-100A, and YF-102 aircraft. The mechanics of gyroscopics, centrifugal effect, and resonance in coupling dynamics are described. The coupling modes discussed are interacting multiple degrees of freedom of inertial and aerodynamic forces and moments. Various solutions for coupling instabilities are discussed.
Determination of Lateral Stability Characteristics from Free-flight Model Tests, with Experimental Results on the Effects of Wing Vertical Position and Dihedral at Transonic Speeds
A test and analysis method is presented for determining airplane lateral stability characteristics, including aerodynamic derivatives, from flight tests of scale models. The method of analysis utilizes the rotating time-vector concept and also a quasi-static approach. Data are presented at transonic speeds for three swept-wing rocket-propelled models differing only in vertical position and dihedral of the wing. The method proved to be adequate for delineating the major effects of the geometric variations on the aerodynamic lateral stability derivatives. The effects of Reynolds number on the linearity of the static stability data for an unswept wing configuration are illustrated.
