Asked by Tony
Please if you could help with this...
and explain very carefully I'll be very thankful.
The dragonfly has a wing chord of 0.01 m, and can fly at 10 m/s. Assume roughly sea level viscosity ν=1.45×10−5m2/s. Determine the momentum thickness θ on the upper and lower surfaces at the trailing edge, again for b=0.05. Specify the results in meters.
Round your answer to two significant digits.
b.What is the overall 2D profile drag for this airfoil in this condition? Round your answer to two significant digits.
c. 5) What is the 2D lift-to-drag ratio for this airfoil in this condition? Round your answer to two significant digits.
and explain very carefully I'll be very thankful.
The dragonfly has a wing chord of 0.01 m, and can fly at 10 m/s. Assume roughly sea level viscosity ν=1.45×10−5m2/s. Determine the momentum thickness θ on the upper and lower surfaces at the trailing edge, again for b=0.05. Specify the results in meters.
Round your answer to two significant digits.
b.What is the overall 2D profile drag for this airfoil in this condition? Round your answer to two significant digits.
c. 5) What is the 2D lift-to-drag ratio for this airfoil in this condition? Round your answer to two significant digits.
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