The performance of an aircraft to fly at an altitude of 2400 m at a speed of 290 km/h will be evaluated using a 1/8 scal

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The performance of an aircraft to fly at an altitude of 2400 m
at a speed of 290 km/h will be evaluated using a 1/8 scale model
tested in a pressurized wind tunnel while maintaining similarity.
The conditions at flight altitude are temperature = -1ºC, pressure
= 75 kN/m2 and μ=17.1 × 10–6 kg/ms. The test conditions are 2150
kN/m2 and 15ºC and μ=18.1 × 10–6 kg/ms. The drag resistance in the
model was measured between 18 m/s and 27 m/s obtaining 4.7N and
9.6N. Determine the drag on the prototype.
The dimensionless groups required for this to be achieved
are: _______ ,
________ y
_______ .
The determined speed of the model is
____ Ms. and the drag with this condition
is _______ N while
prototype drag _____ N. Not
a: The dimensionless group must be placed as the dimensionless
number is known as Eu, Cd, Cp, Cl, among others.