Question: Consider the isentropic flow over an airfoil. The free stream conditions are T = 245 K and p = 4.35x 104 N/m2. At a point

Consider the isentropic flow over an airfoil. The free stream conditions are T∞ = 245 K and p∞ = 4.35x 104 N/m2. At a point on the airfoil, the pressure is 3.6 x 104 N/m2. Calculate the density at this point.

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