when the angle of attack =?, the total lift coefficient begin to decrease suddenly
when the angle of attack =?, the total lift coefficient begin to decrease suddenly. Here, I consider the NACA0012 airfoil, freestream air speed=30m/s
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ehmmm, stall?
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Okay, I misunderstood your question. Well that depends on the Reynolds number, so you need to provide the chord length of your airfoil and the flow conditions (standard athmospheric ?).
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air density =1.225;
temperature T0=273.16; chord length of NACA0012 airfoil is 300mm. freestream air speed=30m/s viscous coefficient mu=1.7161e-5 Reynolds number:70946 |
Quote:
temperature T0=273.16; chord length of NACA0012 airfoil is 300mm. freestream air speed=30m/s viscous coefficient mu=1.7161e-5 Reynolds number:70946 |
velocity inlet in fluent
Dear friends,
In fluent, For analysis of 2D naca0012 airfoil velocity inlet we give vcostheta in x component & vsintheta in y component, v is inlet velocity. 1)here i start analysis of 3D wing, for that i take naca 0012 airfoil & extrude 100mm, in gambit and analysis in fluent i have doubt how to set velocity inlet, here i consider my velocity is 50m/s, then what is xyz component,please let me know. 2)if you consider 3D wing, (vtantheta for z component) is correct or wrong, please let me know. 2) how to find angle of attack for 3D wing? please let me know |
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