The drag of a small aircraft component is to be investigated by testing it in a water tunnel (ρ = 1000 kg/m3 , µ = 1.14x10-3 Ns/m2 ). The speed of the aircraft is 170 m/s at an altitude where the air density is 0.90 kg/m3 and the viscosity is 1.67 x 10-5 Ns/m2 . Estimate the water speed in the tunnel for dynamic similarity, and the ratio of the drag in water to that in air.
The drag of a small aircraft component is to be investigated by testing it in a water tunnel (ρ = 1000 kg/m3 , µ = 1.14x10-3 Ns/m2 ). The speed of the aircraft is 170 m/s at an altitude where the air density is 0.90 kg/m3 and the viscosity is 1.67 x 10-5 Ns/m2 . Estimate the water speed in the tunnel for dynamic similarity, and the ratio of the drag in water to that in air.
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The drag of a small aircraft component is to be investigated by testing it in a water tunnel (ρ
= 1000 kg/m3
, µ = 1.14x10-3 Ns/m2
). The speed of the aircraft is 170 m/s at an altitude where
the air density is 0.90 kg/m3 and the viscosity is 1.67 x 10-5 Ns/m2
.
Estimate the water speed in the tunnel for dynamic similarity, and the ratio of the drag in
water to that in air.
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