if flow separation causes a lower pressure on the top surface of an airfoil then shouldn't lift be augmented because of the higher pressure difference? Why does an aircraft stall instead? Please help. Ive been searching for an answer from a long time
Flow separation does not cause a lower pressure on the top surface of an airfoil. The pressure is lower if the flow remains attached. This is because, if the flow is attached, the streamlines follow the surface shape and are more curved. The more a streamline curves, the greater the pressure gradient across it must be (due to f = m*a), with lower pressure on the inside of the curve.
I was really searching for an explanation of this manner.....tq so much
if flow separation causes a lower pressure on the top surface of an airfoil then shouldn't lift be augmented because of the higher pressure difference? Why does an aircraft stall instead? Please help. Ive been searching for an answer from a long time
Flow separation does not cause a lower pressure on the top surface of an airfoil. The pressure is lower if the flow remains attached. This is because, if the flow is attached, the streamlines follow the surface shape and are more curved. The more a streamline curves, the greater the pressure gradient across it must be (due to f = m*a), with lower pressure on the inside of the curve.