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Fluids/Aerodynamics Problem

Not sure how to approach this problem. Seems simple. Here it is...

An airplane is moving through still air at 60m/s. At some point on the wing, the air pressure is -1200N/m^2 gauge. If the density of air is 0.8kg/m^3, find the velocity of the flow at this point. Carefully list the assumptions you have made in your analysis. Express your answer in terms of nondimensional pressure coefficient Cp.

I can tell you that Cp=(p-pinf)/qinf, where pinf is the free stream pressure and qinf=0.5*freestremdensity*freestreamvelociy^2.

Any help would be much appreciated...
 

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