Question

. Air flows with Mach 2.8 over a flat plate that is set at an angle of 7° to the upstream flow. The pressure in the upstream flow is 100 kPa. Find the lift and drag coefficients using linearized theory.

Answer #1

Solution:

given data

M_{}
= 2.8

= 7^{0} =0.122 radian

lift coefficient using linearized theory can be given as

C_{l} =

**C _{l} = 0.186**

drag coefficient using linearized theory can be given as

C_{d} =

**C _{d} = 0.0227**

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