This paper describes the analysis of the thermal stress concentration and the effects of geometrical shape in the interfacial edge by FEM. It is shown that the elevated stress in a dissim...This paper describes the analysis of the thermal stress concentration and the effects of geometrical shape in the interfacial edge by FEM. It is shown that the elevated stress in a dissimilar material caused by temperature is only restricted in a minor region of the interfacial edge, where the stress peak value and and the stress gradient are high. It is also found that narrowing the boundary angle can effectively reduce the peak value of stress components on the interfacial layer, especially the peeling stress σ y , which is a condition of the debonding failure in the interface.θ=60, an obvious variation, proves that selecting a reasonable edge geometrical shape helps to reduce the value of the maximum stress. At last the methods of relaxing stress concentration and effects of the geometric blunt are also discussed.展开更多
The flow fields over a generic cranked double delta wing were investigated. Pressure and velocity distributions were obtained using a Pitot tube and a hot wire anemometer. Two different leading edge shapes, namely ＂s...The flow fields over a generic cranked double delta wing were investigated. Pressure and velocity distributions were obtained using a Pitot tube and a hot wire anemometer. Two different leading edge shapes, namely ＂sharp＂ and ＂round＂, were applied to the wing. The wing had two sweep angles of 55° and 30°. The experiments were conducted in a closed circuit wind tunnel at velocity 20 m/s and angles of attack of 5°- 20° with the step of 5°. The Reynolds number of the model was about 2 - 105 according to the root chord. A dual vortex structure was formed above the wing surface. A pressure drop occurred at the vortex core and the root mean square of the measured velocity increased at the core of the vortices, reflecting the instability of the flow in that region. The magnitude of power spectral density increased strongly in spanwise direction and had the maximum value at the vortex core. By increasing the angle of attack, the pressure drop increased and the vortices became wider; the vortices moved inboard along the wing, and away from the surface; the flow separation was initiated from the outer portion of the wing and developed to its inner part. The vortices of the wing of the sharp leading edge were stronger than those of the round one.展开更多
文摘This paper describes the analysis of the thermal stress concentration and the effects of geometrical shape in the interfacial edge by FEM. It is shown that the elevated stress in a dissimilar material caused by temperature is only restricted in a minor region of the interfacial edge, where the stress peak value and and the stress gradient are high. It is also found that narrowing the boundary angle can effectively reduce the peak value of stress components on the interfacial layer, especially the peeling stress σ y , which is a condition of the debonding failure in the interface.θ=60, an obvious variation, proves that selecting a reasonable edge geometrical shape helps to reduce the value of the maximum stress. At last the methods of relaxing stress concentration and effects of the geometric blunt are also discussed.
文摘The flow fields over a generic cranked double delta wing were investigated. Pressure and velocity distributions were obtained using a Pitot tube and a hot wire anemometer. Two different leading edge shapes, namely ＂sharp＂ and ＂round＂, were applied to the wing. The wing had two sweep angles of 55° and 30°. The experiments were conducted in a closed circuit wind tunnel at velocity 20 m/s and angles of attack of 5°- 20° with the step of 5°. The Reynolds number of the model was about 2 - 105 according to the root chord. A dual vortex structure was formed above the wing surface. A pressure drop occurred at the vortex core and the root mean square of the measured velocity increased at the core of the vortices, reflecting the instability of the flow in that region. The magnitude of power spectral density increased strongly in spanwise direction and had the maximum value at the vortex core. By increasing the angle of attack, the pressure drop increased and the vortices became wider; the vortices moved inboard along the wing, and away from the surface; the flow separation was initiated from the outer portion of the wing and developed to its inner part. The vortices of the wing of the sharp leading edge were stronger than those of the round one.
