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# 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.
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
{% file src="/files/-MgbFgyytNqYbF6SdTrZ" %}
## 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