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Problem getting lift to drag ratio

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July 10, 2018, 08:37	Problem getting lift to drag ratio	#1
SRaghavendra New Member Raghavendra S Join Date: Jul 2018 Location: Mangalore Posts: 1 Rep Power: 0	I am simulating flow field around SG6043 airfoil at 1,00,000 Reynolds number in FLUENT using unstructured mesh of grid size around 10 lakhs. I am using sphere of influence technique to generate finer mesh near airfoil surface. I am getting stall angle as 16 deg with cl_max of 1.1445 whereas xfoil is showing stall angle as 14 deg with cl_max of 1.6491. Also, in xfoil maximum (cl/cd) is occurring at +6 deg whereas numerical result is showing maximum (cl/cd) at -6 deg. Is this deviation acceptable? If not, how to improve the numerical results?

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lift and drag, numerical error, sphere of influence, stall angle, unstructured mesh

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