An aircraft model is to be used to analyse the aerodynamics of a full size aircraft...

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An aircraft model is to be used to analyse the aerodynamics of a full size aircraft by immersing it in a flow of air in a variable density wind tunnel. The full size aircraft has a wing chord of 3.2 m and is expected to operate at Mach 0.65 at an altitude of 15600 ft, where the dynamic viscosity is 1.6293 x 105 kg/m-s, the air density is 0.7562 kg/m, and the speed of sound is 321.545 m/s. The wind tunnel flow is operated with an airflow at sea level conditions, where the dynamic viscosity is 1.783 x 105 kg/m-s and the speed of sound is 340.292 m/s. If the aircraft model has a wing chord of 0.53 m, what airflow speed and air density should be used for the experiment? An aircraft model is to be used to analyse the aerodynamics of a full size aircraft by immersing it in a flow of air in a variable density wind tunnel. The full size aircraft has a wing chord of 3.2 m and is expected to operate at Mach 0.65 at an altitude of 15600 ft, where the dynamic viscosity is 1.6293 x 105 kg/m-s, the air density is 0.7562 kg/m, and the speed of sound is 321.545 m/s. The wind tunnel flow is operated with an airflow at sea level conditions, where the dynamic viscosity is 1.783 x 105 kg/m-s and the speed of sound is 340.292 m/s. If the aircraft model has a wing chord of 0.53 m, what airflow speed and air density should be used for the experiment?

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To analyze the aerodynamics of an aircraft using a scaled model in a wind tunnel the key is to maintain dynamic similarity between the model and the a... View the full answer