A fl at-plate airfoil with C = 1.2 m is to have a lift of30 kN/m when fl ying at 5000-m standard altitude withU∞= 641 m/s. Using Ackeret theory, estimate (a) the angleof attack and (b) the drag force in N/m.
A fl at-plate airfoil with C = 1.2 m is to have a lift of30 kN/m when fl ying at 5000-m standard altitude withU∞= 641 m/s. Using Ackeret theory, estimate (a) the angleof attack and (b) the drag force in N/m.
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter5: Analysis Of Convection Heat Transfer
Section: Chapter Questions
Problem 5.29P: Air at 20C flows at 1 m/s between two parallel flat plates spaced 5 cm apart. Estimate the distance...
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A fl at-plate airfoil with C = 1.2 m is to have a lift of
30 kN/m when fl ying at 5000-m standard altitude with
U∞= 641 m/s. Using Ackeret theory, estimate (a) the angle
of attack and (b) the drag force in N/m.
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