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Question #3 (Refer to Chapters 18 and 19 for this problem) The wing on a Piper Cherokee general aviation aircraft is rectangular, with a span of 9.75 m and a chord of 1.6 m . The aircraft is flying at cruising speed of 141 mph at sea level ( \rho =1.225k(g)/(m^(3)) and \mu =1.7894\times 10^(-5)k(g)/(ms) ). Assume that the skin friction drag on the wing can be approximated by the drag on a flat plate of the same dimensions. Calculate the skin friction drag, D_(f) (in Newtons): (a) If the flow were completely laminar (which is not the case in real life) (b) If the flow were completely turbulent (which is a bit more realistic). How much larger is this value than the value you found in part (a)? (c) If the flow is assumed to transition at Re_(cr)=5\times 10^(5) (which is closest to reality). How does this value compare to the values you found in parts (a) and (b) ?

          Question #3 (Refer to Chapters 18 and 19 for this problem)
The wing on a Piper Cherokee general aviation aircraft is rectangular, with a span of 9.75 m and a chord of 1.6 m . The aircraft is flying at cruising speed of 141 mph at sea level ( \rho =1.225k(g)/(m^(3)) and \mu =1.7894\times 10^(-5)k(g)/(ms) ). Assume that the skin friction drag on the wing can be approximated by the drag on a flat plate of the same dimensions. Calculate the skin friction drag, D_(f) (in Newtons):
(a) If the flow were completely laminar (which is not the case in real life)
(b) If the flow were completely turbulent (which is a bit more realistic). How much larger is this value than the value you found in part (a)?
(c) If the flow is assumed to transition at Re_(cr)=5\times 10^(5) (which is closest to reality). How does this value compare to the values you found in parts (a) and (b) ?

question 3 refer to chapters 18 and 19 for this problem the wing on a piper cherokee general aviation aircraft is rectangular with a span of 975 m and a chord of 16 m the aircraft is flying 48048

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