Consider a flat plate at an angle of attack of 2° in a Mach 2.2 airflow. (Mach 2.2 is the cruising Mach number of the Concorde supersonic transport.) The length of the plate in the flow direction is 202 ft, which is the length of the Concorde. Assume that the free-stream conditions correspond to a standard altitude of 50,000 ft. The total drag on this plate is the sum of wave drag and skin friction drag. Assume that a turbulent boundary layer exists over the entire plate. The results given in Chap. 4 for skin friction coefficients hold for incompressible flow only; there is a compressibility effect on Cf such that its value decreases with increasing Mach number. Specifically, at Mach 2.2 assume that the Cf given in Chap. 4 is reduced by 20 percent.
(a) Given all the preceding information, calculate the total drag coefficient for the plate.
(b) If the angle of attack is increased to 5°, assuming Cf stays the same, calculate the total drag coefficient.
(c) For these cases, what can you conclude about the relative influence of wave drag and skin friction drag?
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