Question

. Air flows with Mach 2.8 over a flat plate that is set at an angle...

. 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.

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Answer #1

Solution:

given data

M = 2.8

= 70 =0.122 radian

lift coefficient using linearized theory can be given as

Cl =

Cl = 0.186

drag coefficient using linearized theory can be given as

Cd =

Cd = 0.0227

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