Unformatted text preview: the velocity is 850 ft/s. If the test section ﬂow velocity is 780 ft/s, with a pressure and temperature of 1 atm and 505 ◦ R, respectively, calculate the pressure coeﬃcient at the point. (2) If the test section ﬂow velocity is reduced to 100 ft/s, what will the pressure coeﬃcient become (at the same point)? Problem 3. (Problem 5.13 in Anderson) Consider a NACA 1412 airfoil at an angle of attack of 4 ◦ . If the freestream Mach number is 0.8, calculate the lift coeﬃcient. Problem 4. An airfoil is inclined at 5 ◦ degrees angle of attack to the relative ﬂow. The minimum pressure coeﬃcient at low subsonic values is C p, = 0 . 5. Calculate the critical Mach number and corresponding critical pressure coeﬃcient for the airfoil. 1...
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 Fall '09
 Fluid Dynamics, Aerodynamics, 5 degrees, 100 ft, section flow velocity, test section flow

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