Hello Everyone ,
Hope you are doing fine . I have this question about the reference values , that which length should one use while doing external aerodynamic CFD simulation of a full aircraft . The main objective of the simulation is to get the aerodynamic coefficients values at different angle of attacks . Should I be using full length of the aircraft as the resulting boundary layer will be formed over whole of the aircraft length ?
Your kind suggestions in this regard will be really helpful .
Aamir
Dear Aamir,
it depend on the specific aircraft geometry. If I assume that you have a classical tube and wing aircraft, for aerodynamics coefficients values study, you should probably use the wing mean chord as length. However, for the lift and drag coefficients, you should divide the force by the wing surface area. So it is not clear why you need a reference length for your study. If this is for the Reynolds number definition, then you could also use the length of the fuselage instead of the mean chord.
Dear Aamir,
it depend on the specific aircraft geometry. If I assume that you have a classical tube and wing aircraft, for aerodynamics coefficients values study, you should probably use the wing mean chord as length. However, for the lift and drag coefficients, you should divide the force by the wing surface area. So it is not clear why you need a reference length for your study. If this is for the Reynolds number definition, then you could also use the length of the fuselage instead of the mean chord.
François Morency Thank you so much . Yes , I was particularly asking this to calculate the Reynolds number .
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