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Loads on External Stores at Transonic and Supersonic Speeds
Results of recent wind-tunnel investigations of the loads on external stores at transonic and supersonic speeds have shown that the most critical store loading appears to be that due to the store side force, both because of its magnitude and because the force acts in the direction of the least structural strength of the pylon. The magnitude of the side forces is determined principally by angle of attack, store position, and Mach number. Angle of attack and store positions are inextricably related since the rate of change of side force with angle of attack, which can be very large, is primarily a function of position. Also, at moderate angles of attack, the rate of increase of side-force coefficient with angle of attack for a given store position is essentially constant with Mach number. The effects of Mach number are shown principally in the values of the coefficient at small angles of attack. These values are strongly influenced by local angularities and the changes in flow behavior that occur at transonic and supersonic speeds.
Structural Dynamic Experiences of the X-15 Airplane
The structural dynamic problems anticipated during the design of the X-15 airplane are reviewed briefly, and the actual flight experiences with the airplane are described. The noise environment, acoustic fatigue problems, and panel-flutter experiences are discussed. Where these problems led to structural modifications, the modifications are described. (Author).
Flutter Research on Skin Panels
Representative experimental results are presented to show the current status of the panel flutter problem. Results are presented for unstiffened rectangular panels and for rectangular panels stiffened by corrugated backing. Flutter boundaries are established for all types of panels when considered on the basis of equivalent isotropic plates. The effects of Mach number, differential pressure, and aerodynamic heating on panel flutter are discussed. A flutter analysis of orthotropic panels is presented in the appendix.
Flutter Research on Skin Panels
Representative experimental results are presented to show the current status of the panel flutter problem. Results are presented for unstiffened rectangular panels and for rectangular panels stiffened by corrugated backing. Flutter boundaries are established for all types of panels when considered on the basis of equivalent isotropic plates. The effects of Mach number, differential pressure, and aerodynamic heating on panel flutter are discussed. A flutter analysis of orthotropic panels is presented in the appendix.
