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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.

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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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

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agard_ar_303_e6.zip
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