Assignment No. 1 1. An airfoil in a free stream where P. = 0.61 atm, p... = 0.319 Kglm3. and V. = 300 W3. At a point on the airfoil surface, the pressure is 0.5 atm. Assuming isentropic ow, calculate the velocity at that point. 2. An air tank with a nozzle has a pressure of 196.32 KPa and density of 1.9 Kglm3. Outside the converging- diverging nozzle, the pressure is atmospheric and designed to have a Mach No. of 1.0 and 1.5 at the throat and exit respectively. The area at the throat is 0.11m? Calculate the following: (a) Temperature and speed of sound at the tank. (b) Pressure, density, temperature and speed of sound at the throat. (c) Mass ow at the exit