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Can we model flow over an airplane wing with incompressible flow equations? |
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June 29, 2019, 03:36 |
Can we model flow over an airplane wing with incompressible flow equations?
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#1 | |
Senior Member
Join Date: Jan 2018
Posts: 121
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Hi,
As you know, airplanes have an average velocity of 750 km/h which means they have a Mach number of about 0.6. According to NASA: Quote:
Is the solution reliable? How much error can be generated? |
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June 29, 2019, 03:52 |
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#2 | |
Senior Member
Filippo Maria Denaro
Join Date: Jul 2010
Posts: 6,842
Rep Power: 73 |
Quote:
It depends on the flow problem. Check the inlet Mach condition but consider that the flow accelerate along the airfoil and the Mach can reach higher values. If transonic effects can be disregardable, the incompressible formulation could be quite acceptable. A value of the inlet Mach number greater than 0.3 would address towards a compressible formulation. |
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airfoil, airplane, les |
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