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 bref=2b_{ref}=2bref​=2
m and a chord of cref=0.5c_{ref}=0.5cref​=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 α=0\alpha=0α=0
deg 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=−0.13
m, y=−0.26y=-0.26y=−0.26
m, andy=−0.34y=-0.34y=−0.34
m. The experimental results from Samuelsson [1] are shown for comparison.
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Files
agard_ar_303_e6.zip
1MB
Binary
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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