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SD2083 (9.0%) (sd2083-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD2083 (9.0%) (sd2083-il)
Reynolds number: 200,000
Max Cl/Cd: 80.3 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd2083-il-200000.txt
Download as CSV file: xf-sd2083-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD2083 (9.0%)                                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3904   0.08798   0.08464  -0.0399   1.0000   0.0472
  -8.250  -0.4013   0.08532   0.08208  -0.0421   1.0000   0.0476
  -8.000  -0.4206   0.08358   0.08045  -0.0406   1.0000   0.0477
  -7.750  -0.4424   0.08176   0.07869  -0.0393   1.0000   0.0478
  -7.500  -0.4590   0.07950   0.07644  -0.0383   1.0000   0.0479
  -7.250  -0.3909   0.06697   0.06423  -0.0291   0.9982   0.0517
  -7.000  -0.4654   0.07250   0.06921  -0.0423   0.9970   0.0483
  -6.750  -0.4554   0.06570   0.06258  -0.0431   0.9945   0.0499
  -6.500  -0.4358   0.06406   0.06097  -0.0426   0.9911   0.0532
  -6.250  -0.4097   0.05873   0.05548  -0.0496   0.9859   0.0573
  -6.000  -0.3859   0.05083   0.04695  -0.0587   0.9781   0.0624
  -5.750  -0.3618   0.04742   0.04362  -0.0604   0.9745   0.0643
  -5.500  -0.3317   0.04421   0.04029  -0.0635   0.9714   0.0681
  -5.250  -0.3101   0.04003   0.03551  -0.0657   0.9639   0.0765
  -5.000  -0.2814   0.03712   0.03260  -0.0676   0.9605   0.0796
  -4.750  -0.2480   0.03404   0.02907  -0.0705   0.9575   0.0912
  -4.500  -0.2234   0.02556   0.01938  -0.0676   0.9510   0.0425
  -4.250  -0.1905   0.02332   0.01672  -0.0686   0.9474   0.0429
  -4.000  -0.1536   0.02065   0.01348  -0.0697   0.9451   0.0399
  -3.750  -0.1142   0.01890   0.01143  -0.0716   0.9435   0.0393
  -3.500  -0.0913   0.01793   0.01035  -0.0705   0.9365   0.0398
  -3.250  -0.0559   0.01689   0.00925  -0.0719   0.9333   0.0414
  -3.000  -0.0195   0.01603   0.00835  -0.0735   0.9306   0.0450
  -2.750   0.0058   0.01544   0.00773  -0.0730   0.9246   0.0507
  -2.500   0.0357   0.01472   0.00701  -0.0733   0.9196   0.0648
  -2.250   0.0648   0.01320   0.00640  -0.0739   0.9162   0.2664
  -2.000   0.0812   0.01238   0.00642  -0.0721   0.9085   0.4908
  -1.750   0.1002   0.01139   0.00652  -0.0693   0.9039   0.7761
  -1.500   0.2033   0.01099   0.00625  -0.0834   0.9098   0.9793
  -1.250   0.2654   0.01081   0.00588  -0.0905   0.9085   1.0000
  -1.000   0.2920   0.01073   0.00568  -0.0901   0.9024   1.0000
  -0.750   0.3116   0.01079   0.00565  -0.0885   0.8933   1.0000
  -0.500   0.3376   0.01071   0.00545  -0.0878   0.8875   1.0000
  -0.250   0.3572   0.01078   0.00544  -0.0861   0.8779   1.0000
   0.000   0.3822   0.01069   0.00527  -0.0851   0.8717   1.0000
   0.250   0.4031   0.01072   0.00525  -0.0836   0.8621   1.0000
   0.500   0.4260   0.01070   0.00516  -0.0823   0.8541   1.0000
   0.750   0.4497   0.01062   0.00502  -0.0810   0.8460   1.0000
   1.000   0.4720   0.01062   0.00498  -0.0796   0.8364   1.0000
   1.250   0.4968   0.01050   0.00480  -0.0784   0.8290   1.0000
   1.500   0.5197   0.01047   0.00475  -0.0771   0.8186   1.0000
   1.750   0.5431   0.01044   0.00470  -0.0759   0.8085   1.0000
   2.000   0.5680   0.01036   0.00458  -0.0748   0.7996   1.0000
   2.250   0.5923   0.01031   0.00451  -0.0738   0.7892   1.0000
   2.500   0.6163   0.01030   0.00452  -0.0727   0.7779   1.0000
   2.750   0.6410   0.01028   0.00450  -0.0718   0.7667   1.0000
   3.000   0.6659   0.01025   0.00446  -0.0708   0.7550   1.0000
   3.250   0.6908   0.01022   0.00443  -0.0699   0.7420   1.0000
   3.500   0.7155   0.01021   0.00444  -0.0689   0.7273   1.0000
   3.750   0.7399   0.01021   0.00445  -0.0679   0.7106   1.0000
   4.000   0.7645   0.01022   0.00446  -0.0669   0.6921   1.0000
   4.250   0.7888   0.01027   0.00449  -0.0659   0.6710   1.0000
   4.500   0.8127   0.01035   0.00453  -0.0648   0.6465   1.0000
   4.750   0.8360   0.01048   0.00465  -0.0636   0.6175   1.0000
   5.000   0.8584   0.01069   0.00480  -0.0624   0.5826   1.0000
   5.250   0.8800   0.01099   0.00498  -0.0610   0.5418   1.0000
   5.500   0.9001   0.01142   0.00523  -0.0594   0.4945   1.0000
   5.750   0.9188   0.01197   0.00559  -0.0577   0.4439   1.0000
   6.000   0.9367   0.01262   0.00601  -0.0560   0.3939   1.0000
   6.250   0.9544   0.01330   0.00650  -0.0544   0.3491   1.0000
   6.500   0.9726   0.01398   0.00703  -0.0529   0.3088   1.0000
   6.750   0.9901   0.01470   0.00759  -0.0513   0.2683   1.0000
   7.000   1.0073   0.01545   0.00818  -0.0498   0.2275   1.0000
   7.250   1.0241   0.01623   0.00878  -0.0483   0.1866   1.0000
   7.500   1.0408   0.01705   0.00941  -0.0468   0.1473   1.0000
   7.750   1.0571   0.01793   0.01013  -0.0453   0.1137   1.0000
   8.000   1.0697   0.01920   0.01113  -0.0432   0.0680   1.0000
   8.250   1.0744   0.02125   0.01292  -0.0398   0.0349   1.0000
   8.500   1.0836   0.02271   0.01443  -0.0371   0.0282   1.0000
   8.750   1.0951   0.02385   0.01567  -0.0347   0.0254   1.0000
   9.000   1.1037   0.02514   0.01703  -0.0320   0.0235   1.0000
   9.250   1.1092   0.02692   0.01886  -0.0290   0.0221   1.0000
   9.500   1.1192   0.02910   0.02112  -0.0268   0.0212   1.0000
   9.750   1.1354   0.03079   0.02296  -0.0253   0.0208   1.0000
  10.000   1.1532   0.03277   0.02511  -0.0240   0.0202   1.0000
  10.250   1.1717   0.03511   0.02768  -0.0230   0.0200   1.0000
  10.500   1.1879   0.03782   0.03069  -0.0217   0.0199   1.0000
  10.750   1.1979   0.04061   0.03379  -0.0198   0.0199   1.0000
  11.000   1.2017   0.04300   0.03646  -0.0174   0.0195   1.0000
  11.250   1.2017   0.04566   0.03941  -0.0148   0.0193   1.0000
  11.500   1.1978   0.04833   0.04235  -0.0122   0.0189   1.0000
  11.750   1.1922   0.05088   0.04515  -0.0100   0.0183   1.0000
  12.000   1.1808   0.05453   0.04910  -0.0079   0.0185   1.0000
  12.250   1.1659   0.05860   0.05346  -0.0064   0.0188   1.0000
  12.500   1.1497   0.06281   0.05793  -0.0056   0.0189   1.0000
  12.750   1.1309   0.06771   0.06308  -0.0057   0.0192   1.0000
  13.000   1.1117   0.07296   0.06855  -0.0066   0.0194   1.0000
  13.250   1.0900   0.07902   0.07482  -0.0087   0.0196   1.0000
  13.500   1.0685   0.08560   0.08159  -0.0119   0.0196   1.0000
  13.750   1.0474   0.09285   0.08899  -0.0160   0.0199   1.0000
  14.000   1.0245   0.10134   0.09764  -0.0214   0.0201   1.0000
  14.250   1.0011   0.11107   0.10750  -0.0279   0.0204   1.0000
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