Physics, 10.03.2020 22:21 amyaacrawford86
Plot the pressure coefficient distribution (y-axis) versus chord location (x-axis) about the airfoil shape for each Mach Number. Reverse the orientation of the y-axis (negative numbers above the x-axis) such that the curve representing the upper surface distribution is on top and the curve representing the lower surface distribution is on the bottom.
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Plot the pressure coefficient distribution (y-axis) versus chord location (x-axis) about the airfoil...
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