A frequently quoted rule of thumb in aircraft design is that wings should produce about 1000 N of lift per square meter of wing. (The fact that a wing has a top and bottom surface does not double its area.)(a) At takeoff the aircraft travels at 65.0 m/s, so that the air speed relative to the bottom of the wing is 65.0 m/s. Given the sea level density of air to be 1.29 kg/m³, how fast (in m/s) must it move over the upper surface to create the ideal lift?m/s(b) How fast (in m/s) must air move over the upper surface at a cruising speed of 245 m/s and at an altitude where air density is one-fourth that at sea level? (Note that this is not all of the aircraft's lift--some comes from the body of the plane, some from enginethrust, and so on. Furthermore, Bernoulli's principle gives an approximate answer because flow over the wing creates turbulence.)m/st

Given that:Takeoff speed = Relative airspeed (bottom of the wing) = Sea level air density =

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A frequently quoted rule of thumb in aircraft design is that wings should produce about 1000 N of lift per square meter of wing. (The fact that a wing has a top and bottom surface does not double its area.) a. At takeoff, an aircraft travels at 54 m/s, so that the air speed relative to the bottom of the wing is 54 m/s. Given the sea level density of air to be 1.29 kg/m^3, how fast must it move over the upper surface to create the ideal lift? b. How fast must air move over the upper surface at a cruising speed of 242 m/s and at an altitude where air density is one-fourth that at sea level?
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