An airplane with a plan form area of 15m^2 is moving through the air at True Airspeed(TAS) 150 km/.h at 3000 m altitude on a no wind standard day. Use Appendices for atmosphere data.
What is the static free stream pressure at 3000 m altitude and what is the stagnation pressureon leading edge?
What is the equivalent airspeed (EAS)?
At a point on the airfoil upper surface the local velocity is 175 kn/h. What is the local pressure and pressure coefficient at that point?
If suddenly it is subjected to a 30 km/h crosswind (side wind that is perpendicular to the airplane initial velocity), visualize and calculate the resulting true airspeed (TAS)?