ENGG 2230 Lecture Notes - Lecture 16: Piston Pump, Trailing Edge, Reynolds Number

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A submerged object that provides a large normal force to the free stream with little drag. Aircraft wings have a rounded leading edge and a sharp trailing edge to reduce separation which would cause drag. Lift and drag coefficients through the wing: b is the width, c is the chord length (from the leading edge to the trailing edge of the wing) Airfoils of a finite span need to have their lift and drag adjusted from the infinite. Is the angle of attack between the free stream vector and the chord line vector. (cid:1855)= (cid:3045)(cid:3028)(cid:3034) (cid:3117)(cid:3118)(cid:3118: (cid:1855) and (cid:1855) are functions of the angle of attack and the reynolds number, =(cid:3029)(cid:3118)=(cid:3029)(cid:3030, (cid:3117)(cid:3034)+(cid:3117)(cid:3118)(cid:2870)(cid:3034)+(cid:2869)=(cid:3118)(cid:3034)+(cid:3118)(cid:3118)(cid:2870)(cid:3034)+(cid:2870)+ (cid:3033)+ + (cid:3047, (cid:3033) is friction losses, is minor losses, is the pump head, (cid:3047) is the turbine head. The ratio of lift to drag coefficients on most aircraft is between 20 and 50.

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