For a given airfoil, the critical mach number is 0.8. calculate the value of p/p[infinity]. at the minimum pressure point when m[infinity] = 0.8.

At the point of minimum pressure,

Solution:

As per the question;

Critical Mach no. for the air foil,

= 0.8

Now, for the value of the minimum pressure point:

Pressure of the air foil is critical, when

Now,

         (1)

When M = 1:

                          (2)

When :

                  (3)

Now, from the eqns (1), (2) and (3):

answer:

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explanation:

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explanation: