Transition prediction of the supersonic boundary layer on a cone with small angle of attack and Mach number 3.5 is investi-gated under the consideration of receptivity to slow acoustic waves, as the acoustic waves are...Transition prediction of the supersonic boundary layer on a cone with small angle of attack and Mach number 3.5 is investi-gated under the consideration of receptivity to slow acoustic waves, as the acoustic waves are the main environmental distur-bances in a conventional, i.e. non-quiet, wind tunnel. It is shown that the e-N method can still yield fairly satisfactory results incomparison with those obtained in wind tunnel experiments, provided that the boundary layer receptivity to slow acousticwaves is properly taken into account, including the dependence of the amplitude of disturbances on the frequency andstream-wise location. Neither the conventional e-N method nor the improved e-N method can yield correct result of transitionprediction, because the receptivity mechanisms considered there are not in accord with the real situation in the wind tunnel.展开更多
This paper provides background information on fatigue and describes the methodology used in Creo Simulation （Pro/Mechanica） fatigue analysis. It covers history and physics of fatigue, the E-N approach-Strain Cycles ...This paper provides background information on fatigue and describes the methodology used in Creo Simulation （Pro/Mechanica） fatigue analysis. It covers history and physics of fatigue, the E-N approach-Strain Cycles Includes the effect of mean residual stresses, hysteresis loop capture and rainflow cycle counting. Factors that affect fatigue life include component size, loading type, surface finish, surface treatment and effect of surface treatments on endurance limit. This paper describes practical problem solution and fatigue strength analysis of the wing-hinge to fuselage connection in Creo Simulation （Pro/Mechanica） environment. It also includes a procedure for calculating the buckling load factor and failure index.展开更多
基金supported by the National Natural Science Foundation of China (Grant Nos. 10632050 and 11002098)the National Basic Research Program of China (Grant No. 2009CB724103)the Specialized Research Fund for the Doctoral Program of Higher Education
文摘Transition prediction of the supersonic boundary layer on a cone with small angle of attack and Mach number 3.5 is investi-gated under the consideration of receptivity to slow acoustic waves, as the acoustic waves are the main environmental distur-bances in a conventional, i.e. non-quiet, wind tunnel. It is shown that the e-N method can still yield fairly satisfactory results incomparison with those obtained in wind tunnel experiments, provided that the boundary layer receptivity to slow acousticwaves is properly taken into account, including the dependence of the amplitude of disturbances on the frequency andstream-wise location. Neither the conventional e-N method nor the improved e-N method can yield correct result of transitionprediction, because the receptivity mechanisms considered there are not in accord with the real situation in the wind tunnel.
文摘This paper provides background information on fatigue and describes the methodology used in Creo Simulation （Pro/Mechanica） fatigue analysis. It covers history and physics of fatigue, the E-N approach-Strain Cycles Includes the effect of mean residual stresses, hysteresis loop capture and rainflow cycle counting. Factors that affect fatigue life include component size, loading type, surface finish, surface treatment and effect of surface treatments on endurance limit. This paper describes practical problem solution and fatigue strength analysis of the wing-hinge to fuselage connection in Creo Simulation （Pro/Mechanica） environment. It also includes a procedure for calculating the buckling load factor and failure index.
