Unformatted text preview: number is 0.82. Problem 5.23 A small business jet has a wing area of 21.5 m 2 and an aspect ratio of 5. Assume the wing has a NACA 65-210 airfoil, a span efficiency factor of 0.9, and a profile drag coefficient of 0.004. Calculate the wing lift and drag coefficients if the wing is operating at 6 degree angle-of-attack. Problem 5.26 A light airplane weighs 2,650 lbs and has a wing area of 174 ft 2 . Estimate its sea level stall speed if the maximum lift coefficient is 1.8....
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- Fall '08
- Aerodynamics, 4 degrees, 25,000 ft, 700 ft, 6 degree, 2,650 lbs