Air flows over the airfoil shown in Fig. P3.20. Sensors give the pressures shown at points \(A, B, C\), and \(D\). Find the air velocities just above points \(A, B, C\), and \(D\). The air density is 0.0020 slug \(/ \mathrm{ft}^{3}\).

\(\xrightarrow[p_{0}=13.20 \text { psia }]{V_{0}=100 \mathrm{mph}}\)

Figure P3.20

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Vo=100 mph Po= 13.20 psia A B PA = 13.35 psia Pa = 12.5 psia Pc= 12.8 psia PD= 13.0 psia C D