Dry air at 270C flows with a velocity of 360 kmph in an adiabatic wind tunnel. The static pressure is measured as 110kPa. Determine the Mach number, Stagnation temperature stagnation pressure and the stagnation density of air at the stagnation point on the nose tip of an aircraft model installed in the tunnel. Assume the cross-section area of the tunnel is 1.0 sq.m, Determine the mass flow rate of the air. For air take R = 287 J/kg; = 1.4

Answer rating: 100% (QA)

To solve this problem we can use the following equations 1 Mach number M M Va where V is the velocit... View the full answer