Research Summary for September 20, 2002

A. MDO/HPCCP related:

1.    Final version of the NSF grantees meeting presentation is ready.

·        Click here for the PowerPoint version of the NSF grantees presentation.

·        Click here for the PDF version of the NSF grantees presentation.

 

2.     I am reviewing the airfoil case (RAE 2822 airfoil) in case we decide to include some of the results in the journal paper. We don’t have a detailed study for the airfoil case, but we can support some of the results from the diffuser case. Figure 1 and Table 1 both show that the flow structure has an effect on the grid convergence. We may say that this is a general result observed both for the internal and the external flow problems.

 

   

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

Figure 1. CL vs. h (measure of grid spacing) obtained with the Sp-Al model and the Min-Mod limiter for the RAE 2822 cases with Mach=0.30, Re=6.2x10 6, a=0.0 deg, and Mach=0.75, Re=6.2x106, a=3.19 deg.

Table 1. CL and CD values obtained for two RAE 2822 cases (Sp-Al model and Min-Mod limiter).

          

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

 

B. BWB related:

·        Noise problem for clean wing:

 

1.    Consider parametric pressure distributions for simple 2-D case. Obtain TKE distribution and max TKE value at the trailing edge for different pressure distributions.  (Boundary Layer Applet with TKE model)

 

Figure 2.  Parametric pressure distributions with CLupper=1.0. (XB: The break point from constant Cp)

 

2.    For 3-D case, possible starting point (baseline geometry) may be ONERA M6, since we have some experimental data and grid (from NPARC validation archive) available. After examining the results of the original geometry, a parametric study similar to 2-D case can be made by changing the wing geometry. (GASP)