Abstract
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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