At a given point on the surface of wing flow velocity is 150 m/sec. What is the pressure coefficient at this point? The velocity of an aircraft is 100 m/sec.
The velocity of an aircraft is 100 m/sec. At a given point on the surface of wing flow velocity is 150 m/sec. What is the pressure coefficient at this point?
Considering the flow to be inviscid and incompressible, Pressure coefficient \({{\rm{C}}_{\rm{p}}} = 1 – {\left( {\frac{v}{{{v_\infty }}}} \right)^2}\)\[ = 1 – {\left( {\frac{{150}}{{100}}} \right)^2}\]\[ = – 1.25\]
