An airplane flies at a speed of 400 mph at an altitude of 10,000 ft. if the boundary layers on the wing surfaces behave as those on a flat plate, estimate the location on the wing (i. e., the distance x from the leading edge) where the flow transitions to turbulent flow. assume that the critical reynolds number at which the flow transitions from laminar to turbulent flow is given as rexcr=5x105. if the airplane maintains its 400 mph speed by descends to sea level elevation, will the portion of the wing covered by a laminar boundary layer increase or decrease relative to its value at 10,000 ft.? explain!