AGARD-AR-303 E6

Example simulation of a fixed-wing configuration

An axisymmetric nacelle mounted in the centre of a wing with a span of $b_{ref}=2$ m and a chord of $c_{ref}=0.5$ m with a NACA63(10)A-012 airfoil is considered. Experiments of such configuration were performed by Samuelsson [1] at an angle of attack $\alpha=0$ deg and Reynolds number of $Re=1.14\times10^6$ 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.

Files

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

Files

1MB

agard_ar_303_e6.zip

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 at $y=-0.13$ m, $y=-0.26$ m, and $y=-0.34$ m. The experimental results from Samuelsson [1] are shown for comparison.