Rectangular Supercritical Wing Results: α = 2°, unforced system Sept 11, 2013 JH

Mach 0.825, Re_c = 4M, Test medium: R-12

The unforced system is often referred to as the "steady" or "static" results. The results shown on this page are for the mean angle of attack condition of 2°. The legend or key for the plots is shown at the left of the table. Note that the legend changes for each analysis/test condition. (i.e. it does not apply to the results on other pages.)

 

The principal comparison quantities generated from post-processing the computational outputs are the pressure coefficient distributions. Other quantities calculated include the integrated force (lift & drag) and moment (pitching moment) coefficients.

 

Pressure coefficient distributions

Station 1 η= 0.309 Station 2 η= 0.588 Station 3 η= 0.809 Station 4 η= 0.951 Upper Surface Station 1, η= 0.309 Station 2, η= 0.588 Station 3, η= 0.809 Station 4, η= 0.951 Lower Surface Station 1, η= 0.309 Station 2, η= 0.588 Station 3, η= 0.809 Station 4, η= 0.951

 
 

 

Grid Convergence, lift coefficient

  The integrated loads were computed by each analyst. However, there was confusion over the integration area and the normalizing constants. This confusion is likely responsible for the scatter seen in these results, rather than something inherent in the simulations.

Plotting vs grid factor, grids with more points are towards the left side of the graph (the vertical axis), and smaller grids are out to the right.

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  Lift Coefficient vs Grid Factor

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  Lift Coefficient vs Number of Grid Points, log scale

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  Grid Sizes used

 

 

 

 

Statistical Analysis of Integrated Coefficients

  The submitted integrated load coefficient results were statistically analyzed using the methods applied to the Drag Prediction Workshop (DPW) data and the High Lift Prediction Workshop (HiLPW) data.
 

Lift Coefficient	Drag Coefficient	Pitching Moment Coefficient
Station 2, η= 0.588	Station 2, η= 0.588	Station 2, η= 0.588

 

 

 

 

 

 

Shock properties

  The submitted pressure coefficient results were further analyzed to quantify the predicted shock location & strength for each case.

Station 1 η= 0.309 Station 2 η= 0.588 Station 3 η= 0.809 Station 4 η= 0.951 Shock Location, Upper Surface Station 1, η= 0.309 Station 2, η= 0.588 Station 3, η= 0.809 Station 4, η= 0.951 Shock Strength, Upper Surface Station 1, η= 0.309 Station 2, η= 0.588 Station 3, η= 0.809 Station 4, η= 0.951