11 An aircraft flies at a Mach number of 0.85 at an altitude where the pressure is 7160 N/m² and the temperature is -56.5 °C. A model of the aircraft at 1/10th scale is to be tested in a high- speed wind tunnel representing the flight. The dynamic viscosity of the air can be assumed to be proportional to the 3/4 power of absolute temperature (μ~T%). The temperature of the air inside the wind tunnel is 9 °C. If the air can be assumed as a perfect gas, calculate the velocity, density, and pressure of the airflow in the wind-tunnel such that the lift and drag coefficients are the same between the wind-tunnel model and the actual aircraft in the flight above. Note: absolute temperature (K) = temperature (°C) + 273.15