A supersonic wind tunnel is in the design stage. It is to be driven by a large upstream reservoir of compressed air and discharges to atmospheric conditions downstream. The test section has a constant cross-sectional area and lies downstream of a throat, which is a converging-diverging section that serves to accelerate the flow to supersonic conditions. For the duration of any given experiment, the reservoir can be considered to have constant stagnation conditions that are To = 313K and po = 6105 Pa. The specific gas constant R = 287 J kg-1 K-1 and the specific heat ratio is y = 1.4. = 1.2 m and Mach number M (test section ) = 2.0. The wind tunnel test section is designed to run with a cross-sectional area A ( test section) Find the area of the throat that lies between the reservoir and the test section. Give your answer as a positive value in m to two decimal places.