基于主动动机模型(the model of proactive motivation),本研究探讨了差异化授权领导如何以及何时影响员工的主动服务绩效。以来自两家中高档酒店的321位员工和92位团队领导为样本,通过问卷配对、采用跨层次分析方法,研究发现,差异化授...基于主动动机模型(the model of proactive motivation),本研究探讨了差异化授权领导如何以及何时影响员工的主动服务绩效。以来自两家中高档酒店的321位员工和92位团队领导为样本,通过问卷配对、采用跨层次分析方法,研究发现,差异化授权领导通过负向影响员工的和谐激情,降低了员工的主动服务绩效。员工权力距离感削弱了差异化授权领导对员工和谐激情的负面影响,即权力距离感低时,差异化授权领导与员工和谐激情的负向关系更强,权力距离感高时,负向关系则不显著。最终,本研究建立了一个被调节的中介模型,即权力距离感调节差异化授权领导通过和谐激情对员工主动服务绩效的间接负向影响。展开更多
Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting...Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°–16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack.展开更多
文摘基于主动动机模型(the model of proactive motivation),本研究探讨了差异化授权领导如何以及何时影响员工的主动服务绩效。以来自两家中高档酒店的321位员工和92位团队领导为样本,通过问卷配对、采用跨层次分析方法,研究发现,差异化授权领导通过负向影响员工的和谐激情,降低了员工的主动服务绩效。员工权力距离感削弱了差异化授权领导对员工和谐激情的负面影响,即权力距离感低时,差异化授权领导与员工和谐激情的负向关系更强,权力距离感高时,负向关系则不显著。最终,本研究建立了一个被调节的中介模型,即权力距离感调节差异化授权领导通过和谐激情对员工主动服务绩效的间接负向影响。
文摘Spark discharge plasma synthetic jets(SPJs) have been used for the active flow control study on an NACA 0021 straight-wing model in a wind tunnel. The model forces and moments were measured using a six-component sting balance at a 20 m/s wind speed. The aim was to explore the SPJ's effect on airfoil aerodynamic by examining SPJ generators' position along the chordwise and the jet flow direction about the chord. Near the wing leading edge, two SPJ generators raised the stall angle by 2° and increased the maximum lift coefficient by 9%. The drag coefficient was decreased by 33.1%, and the lift-drag ratio was increased by 104.2% at an angle of attack above 16°. The rolling-moment coefficient was modified by 0.002, and the yawing-moment coefficient was changed by 0.0007 at angles of attack in the range of 0°–16°. The results showed that SPJs can control wing aerodynamic forces at a high angle of attack and moments at a low angle of attack.
