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Unformatted text preview: the velocity is 850 ft/s. If the test section ow velocity is 780 ft/s, with a pressure and temperature of 1 atm and 505 R, respectively, calculate the pressure coecient at the point. (2) If the test section ow velocity is reduced to 100 ft/s, what will the pressure coecient 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 coecient. Problem 4. An airfoil is inclined at 5 degrees angle of attack to the relative ow. The minimum pressure coecient at low subsonic values is C p, = 0 . 5. Calculate the critical Mach number and corresponding critical pressure coecient for the airfoil. 1...
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 Fall '09

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