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THE airfoil CP PLOT IN FLUENT IS JUST NOT POSSIBLE

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Old   February 5, 2008, 20:27
Default THE airfoil CP PLOT IN FLUENT IS JUST NOT POSSIBLE
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Rif
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Hi, i'm running an airfoil simulation in the cfd code Fluent. After my solutions converged, i viewed the Coefficient of pressure plot for my aerofoil. The maximum Cp is more than 1. This does not make sense according to Bernoulli's equations. Can anybody help?

Rif
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Old   February 6, 2008, 06:54
Default Re: THE airfoil CP PLOT IN FLUENT IS JUST NOT POSS
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Charles
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Did you set the right reference values? Also, depending on how far away your boundaries are, and exactly what BC's you specify, it is possible to get a horisontal pressure gradient effect that would show up in a slightly higher stagnation pressure coefficient.
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Old   February 6, 2008, 10:15
Default Re: THE airfoil CP PLOT IN FLUENT IS JUST NOT POSS
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Praveen. C
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If it is compressible flow, then you can get more than one. Back to basic gas dynamics, read Anderson or some such book.
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Old   February 6, 2008, 12:13
Default Re: THE airfoil CP PLOT IN FLUENT IS JUST NOT POSS
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Rif
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It is NOT a compressible flow. My density is constant.

Rif
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