The lower surface typically experiences higher pressure than the upper surface, but the distribution is relatively mild compared to the upper surface. At the leading edge, the airflow directly impacts the airfoil, causing a stagnation point where velocity is zero and pressure is maximum (Cp≈1). Understanding wall pressure distribution is essential in designing efficient airfoils for applications in aviation, wind energy, and even sports engineering. With turbulentboundary layers, the calculation requires cells with very smalllengths normal to the wall to be accurate.
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