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ONERA M-6 wing is definitive CFD validation case for peripheral flows. Due to the reason of its unpretentious geometry associated with intricacies of transonic flow (i.e. local supersonic flow, shocks and turbulent boundary layers’ separation). Transonic flow over the swept wing ONERA M-6 has been studied. The location of shock waves and the supersonic region on the wing is computationally analyzed. Over the years it has practically developed a standard for CFD codes since of its admittance as a validation case in frequent CFD research papers. A 3D flow simulation was accomplished in Fluent® on ONERA M6 wing by using S-A turbulence model. Flow was modelled as being transonic and compressible at an AOA of 3.06 degrees with Reynolds number of 11.72e+6 having Mach of 0.8395. The CFD results thus obtained will be validated against the experimental data that are available for 1/5th span wise location of the wing

Muhammad Umer Sohail, Asad Islam. (2017) Verification and Validation of Flow Over a 3D ONERA Wing using CFD Approach, Journal of Space Technology , Volume 7, Issue 1.
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