Question 8: Consider a steady air flow of velocity, U = 15 m/s, (parallel to the x-axis) over a flat tailed delta wing with the length of 1 m and span of 4 m as shown in the following figure. y 0.8 m 1 1.6 m 0.4 m x 0.4 m y U 0.8 m 1.6 - Ytr Ytr -0.4 0.4 m x 1.6 m Ltr 1 m 1 m The skin friction coefficient of flat plate can be expressed in term of Reynolds number, Rex, for laminar, and turbulent flow as, C = 0.664 (Rex), for, Rex 5 105, and, C = 0.02708 (Rex), for, Rex > 5 105, respectively. Assume air density, p = 1.23 kg/m and kinematic viscosity, v = 1.5 x 10-5 m/s. (a) Calculate the corresponding Reynolds number of the flow. (b) Find the transition length, which measure the distance from the leading edge. (c) Determine the drag force applied on the delta wings (include upper and lower surface). (d) Repeat the problem if the velocity of air flow, U =