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Consider a constant density gas flowing steadily over an airfoil. Far upstream the velocity is V0. Halfway along the top surface, the velocity has increased to 2V0. Halfway along the bottom surface, the
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Consider a constant density gas flowing steadily over an airfoil. Far upstream the velocity is V0. Halfway along the top surface, the velocity has increased to 2V0. Halfway along the bottom surface, the velocity has decreased to V0/2. Find the pressure difference between the top and bottom surface at this location. State all your assumptions.

User Zirak
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The solution and complete explanation for the above question and mentioned conditions is given below in the attached document.i hope my explanation will help you in understanding this particular question.

Step-by-step explanation:

Consider a constant density gas flowing steadily over an airfoil. Far upstream the-example-1
User Danqi Wang
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