[mm391]

Hello,

I am doing a CFD investigation on an RAE 2822 Aerofoil using density based and the K-Omega SST model. I have got a result, which looks good apart from the locations of the shockwave.

The shockwave seems to happen earlier on the topside of the aerofoil in my CFD than in the experimental data i've got. I have refined my mesh considerably around the region but nothing seems to correct it. The Reynolds number is 6.5e+06 at Mach 0.725. I worked out my speed to be 246.7001 m/s given a temp of 288 kelvin and 1 atmosphere, giving me a chord length of 0.3855. The only reason I can think my shockwave maybe wrong is because I have miss calculated the chord length.

Can anyone suggest something I may be over looking? I have attached a matlab picture of the pressure coefficient vs. aerosol length. The experimental data is the red line and my data is in blue.

Many Thanks

Mark
p.s I am using Fluent to solve and created an unstructured mess with an inflation layer that has a Yplus value that fall within the correct parameters.