Discussion
At a point on an airfoil the local velocity is \(1.3\) times the free-stream value. In incompressible flow the pressure coefficient there is
Answer: C
Correct answer: -0.69
For incompressible flow the pressure coefficient follows from the velocity ratio alone: \[ C_p = 1 - \left(\frac{V}{V_\infty}\right)^2 = 1 - 1.3^2 = 1 - 1.69 = -0.69. \] The negative sign says the local pressure is below free stream, which is what an accelerated flow must produce. Anywhere the flow speeds up, \( C_p \) is negative; only at a stagnation point, where \( V = 0 \), does it reach its maximum of \( +1 \).
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