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/m^3 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 1 atm=1.01*10^5n/m^2. calculate the necessary velocity, temperature, and density of the airflow in the wind-tunnel test section such that the lift and drag coefficients are the same for the wind-tunnel model and the actual airplane in flight.