P1= 0.7545 atm M1= ? M„= 0.6 P.=1 atm Figure 8.5 Figure for Example 8.2.
Consider an airfoil in a flow at standard sea level conditions with a freestream velocity of 50 m/s. At a given point on the airfoil, the pressure is 0.9 × 105 N/m2.
As shown above,we illustrated for an incompressible flow, the calculation of the velocity at a point on an airfoil when we were given the pressure at that point and the freestream velocity and pressure. The solution involved the use of Bernoulli’s equation. Let us nowexamine the compressible flow analog above. Consider an airfoil in a freestream where M∞ = 0.6 and p∞ = 1 atm, as sketched in 8.5. At point 1 on the airfoil the pressure is p1 = 0.7545 atm. Calculate the local Mach number at point 1. Assume isentropic flow over the airfoil.
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