The drag coefficient associated with a particular aircraft wing section is measured in a wind tunnel using 1/4 scale model. The model is tested at 300K and 100kPa. The full size aircraft flies at 58.1 m/s at an altitude of 6000m, where temperature and pressure are 250K and 47kPa respectively. Viscosity of air at 300K is 18.537x10^-6 Pa-s and at 250K is 16.03x10^-6 Pa-s. What is the wind tunnel speed required for the Reynolds number of the model to match that of the full size aircraft?