Consider a Lear jet flying at a velocity of 250 m/s at an altitude of 10 km, where the density and temperature are 0.414 kg/m³ and 223 K, respectively. Consider also a one-fifth scale model of the Lear jet being tested in a wind tunnel in the laboratory. The pressure in the test section of the wind tunnel is 1atm = 1.01 x 10⁵ N/m². Calculate the necessary velocity, temperature, and density of the airflow in the wind-tunnel test section such that the lift a id drag coefficients are the same for the wind-tunnel model and the actual airplane in flight. Note: The relation among pressure, density, and temperature is given by the equation of state described in Prob. 1.1.