The drag characteristics of an airplane are to be determined by model tests in a wind tunnel operated at an absolute pressure of 1300 kpa. if the prototype is to cruise in standard air at 385 km/hr, and the corresponding speed of the model is not to defer by more than 20% from this (so that compressibility effects may be ignored), what range of length scales may be used if reynolds number similarity is to be maintained? assume the viscosity of air is unaffected by pressure, and the temperature of air in the tunnel is equal to the temperature of the air in which the airplane will fly.