Dynamic pressure at stag point for 3d aerofoil
hi all, im modeeling flow around a 3d aerofoil section. at the stagnation point on the leading edge, fluent reads that velocity is zero as expected. however it also tells me that local dynamic pressure at the same point is +27Pa. this is completely baffling me. if anyone has any ideas they would be greatly appreciated. thanks

Re: Dynamic pressure at stag point for 3d aerofoil
CHECK THE REFERENCE VULLES.DRAW THE WALL SHEAR STRESS PLEASE, SENT TO ME THE JOURNAL FILE OF THE FLUENT AND GAMBIT FOR CHECK. MOHAMED HASSAN M75202@YAHOO.COM

Re: Dynamic pressure at stag point for 3d aerofoil
Rounding errors. Use the double precision solver and see the value you get. The velocity is zero because it is a Wall (i.e u=v=w=0) but the dynamic head is the result of multiplying the density times velocity times velocity times 0.5

Re: Dynamic pressure at stag point for 3d aerofoil
Hi, thanks for this. i altered the reference point and got a result, however my pressure coefficient is now ~1.3 at the leading edge?! what files may i send you? the .jou and a .xy file of the wall shear over the aerofoil. thanks much. Matt

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