A 40% scale model of an aircraft is to be tested in a flow regime where unsteady flow effects are important. The full-scale vehicle experiences the unsteady effects at a Mach number of 1.00 at an altitude of 12,000 m. The model is to be tested at 22°C and noting that the speed of sound is proportional to the square root of the temperature, determine the temperature that the model must be tested at to produce an equal Reynolds number.