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Calculate the lift and drag coefficients of a flat plate flying in air at Mach 3...

Calculate the lift and drag coefficients of a flat plate flying in air at Mach 3 for angles-of-attack 0-20 using these equations Cl=L/.(5*gamma*p*M^2*c)

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There are assumptions involved as tgere are less values. Please give a thimps up

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