airfoil - What is the effect of flow separation on lift, pressure
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Consider an airfoil (a wing) in an airflow. When angle of attack increases, at some point the flow start to separate from trailing edge. By increasing the angle of attack more, this separation area
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a) What is an adverse pressure gradient and where does it occur on an airfoil? (b) What causes the flow to separate from an airfoil? (c) What are the two major consequences
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