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AGARD-AR-303 E6

Example simulation of a fixed-wing configuration

PreviousNREL Phase IV wind turbineNextWing-tail configuration

Last updated 11 months ago

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An axisymmetric nacelle mounted in the centre of a wing with a span of bref=2b_{ref}=2bref​=2m and a chord of cref=0.5c_{ref}=0.5cref​=0.5m with a NACA63(10)A-012 airfoil is considered. Experiments of such configuration were performed by Samuelsson [1] at an angle of attack α=0\alpha=0α=0deg and Reynolds number of Re=1.14×106Re=1.14\times10^6Re=1.14×106 based on the length of the nacelle. An unstructured grid with 19024 elements is used. The images below show the mesh and the pressure coefficient distribution.

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References

[1] Samuelsson, I. "Experimental Investigation of Low Speed Model Propeller Slipstream Aerodynamic Characteristics Including Flow Field Surveys and Nacelle/Wing Static Pressure Measurements", 1990

The images below show the pressure coefficient aty=−0.13y=-0.13y=−0.13m, y=−0.26y=-0.26y=−0.26m, andy=−0.34y=-0.34y=−0.34m. The experimental results from Samuelsson [1] are shown for comparison.

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agard_ar_303_e6.zip
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