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SG6051 (sg6051-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SG6051 (sg6051-il)
Reynolds number: 200,000
Max Cl/Cd: 82.21 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sg6051-il-200000.txt
Download as CSV file: xf-sg6051-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SG6051                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4048   0.09125   0.08804  -0.0457   1.0000   0.0480
  -8.750  -0.4307   0.09049   0.08738  -0.0412   1.0000   0.0479
  -8.500  -0.4447   0.08789   0.08484  -0.0409   0.9983   0.0484
  -8.250  -0.4399   0.08149   0.07845  -0.0495   0.9922   0.0501
  -8.000  -0.4313   0.07065   0.06749  -0.0667   0.9844   0.0518
  -7.750  -0.4510   0.05084   0.04699  -0.0787   0.9745   0.0321
  -7.500  -0.4345   0.04362   0.03928  -0.0829   0.9712   0.0314
  -7.250  -0.4211   0.03792   0.03302  -0.0840   0.9644   0.0312
  -7.000  -0.3970   0.03199   0.02635  -0.0859   0.9611   0.0311
  -6.750  -0.3667   0.02761   0.02117  -0.0874   0.9587   0.0326
  -6.500  -0.3415   0.02477   0.01791  -0.0877   0.9538   0.0355
  -6.250  -0.3104   0.02404   0.01699  -0.0887   0.9493   0.0413
  -6.000  -0.2780   0.02271   0.01552  -0.0903   0.9461   0.0486
  -5.750  -0.2442   0.02155   0.01413  -0.0919   0.9436   0.0568
  -5.500  -0.2189   0.02116   0.01366  -0.0917   0.9371   0.0632
  -5.250  -0.1885   0.01999   0.01225  -0.0923   0.9328   0.0678
  -5.000  -0.1572   0.01901   0.01126  -0.0931   0.9296   0.0730
  -4.750  -0.1308   0.01844   0.01057  -0.0929   0.9238   0.0774
  -4.500  -0.1034   0.01759   0.00966  -0.0928   0.9187   0.0817
  -4.250  -0.0745   0.01694   0.00903  -0.0931   0.9149   0.0885
  -4.000  -0.0484   0.01651   0.00853  -0.0928   0.9092   0.0945
  -3.750  -0.0222   0.01594   0.00801  -0.0926   0.9038   0.1048
  -3.500   0.0057   0.01540   0.00750  -0.0926   0.8999   0.1215
  -3.250   0.0310   0.01471   0.00708  -0.0926   0.8943   0.1703
  -3.000   0.0543   0.01355   0.00696  -0.0925   0.8888   0.4279
  -2.750   0.0807   0.01322   0.00684  -0.0921   0.8849   0.5045
  -2.500   0.1061   0.01304   0.00685  -0.0917   0.8793   0.5636
  -2.250   0.1311   0.01280   0.00684  -0.0910   0.8738   0.6318
  -2.000   0.1550   0.01249   0.00680  -0.0897   0.8699   0.7152
  -1.750   0.1745   0.01233   0.00696  -0.0872   0.8640   0.8164
  -1.500   0.2000   0.01227   0.00703  -0.0856   0.8588   0.9209
  -1.250   0.2647   0.01225   0.00694  -0.0929   0.8567   0.9956
  -1.000   0.2970   0.01223   0.00677  -0.0940   0.8526   1.0000
  -0.750   0.3199   0.01234   0.00679  -0.0935   0.8454   1.0000
  -0.500   0.3442   0.01232   0.00666  -0.0927   0.8406   1.0000
  -0.250   0.3687   0.01243   0.00668  -0.0923   0.8347   1.0000
   0.000   0.3938   0.01250   0.00668  -0.0919   0.8286   1.0000
   0.250   0.4201   0.01249   0.00658  -0.0914   0.8245   1.0000
   0.500   0.4457   0.01266   0.00672  -0.0913   0.8177   1.0000
   0.750   0.4723   0.01270   0.00670  -0.0910   0.8123   1.0000
   1.000   0.4997   0.01270   0.00662  -0.0907   0.8086   1.0000
   1.250   0.5256   0.01290   0.00683  -0.0907   0.8008   1.0000
   1.500   0.5531   0.01289   0.00677  -0.0905   0.7959   1.0000
   1.750   0.5799   0.01300   0.00687  -0.0904   0.7896   1.0000
   2.000   0.6070   0.01303   0.00689  -0.0902   0.7831   1.0000
   2.250   0.6351   0.01299   0.00681  -0.0900   0.7783   1.0000
   2.500   0.6615   0.01311   0.00697  -0.0899   0.7699   1.0000
   2.750   0.6899   0.01302   0.00684  -0.0897   0.7648   1.0000
   3.000   0.7163   0.01312   0.00699  -0.0896   0.7557   1.0000
   3.250   0.7449   0.01299   0.00683  -0.0893   0.7499   1.0000
   3.500   0.7713   0.01306   0.00695  -0.0891   0.7401   1.0000
   3.750   0.7992   0.01300   0.00689  -0.0889   0.7325   1.0000
   4.000   0.8265   0.01295   0.00687  -0.0886   0.7229   1.0000
   4.250   0.8534   0.01295   0.00691  -0.0883   0.7125   1.0000
   4.500   0.8811   0.01288   0.00686  -0.0881   0.7027   1.0000
   4.750   0.9086   0.01279   0.00679  -0.0877   0.6913   1.0000
   5.000   0.9350   0.01277   0.00682  -0.0873   0.6779   1.0000
   5.250   0.9614   0.01274   0.00684  -0.0868   0.6633   1.0000
   5.500   0.9878   0.01271   0.00682  -0.0863   0.6469   1.0000
   5.750   1.0129   0.01276   0.00693  -0.0857   0.6269   1.0000
   6.000   1.0381   0.01282   0.00700  -0.0850   0.6049   1.0000
   6.250   1.0620   0.01295   0.00713  -0.0842   0.5765   1.0000
   6.500   1.0844   0.01319   0.00730  -0.0830   0.5403   1.0000
   6.750   1.1051   0.01359   0.00757  -0.0817   0.4963   1.0000
   7.000   1.1227   0.01422   0.00797  -0.0799   0.4424   1.0000
   7.250   1.1366   0.01511   0.00858  -0.0777   0.3806   1.0000
   7.500   1.1466   0.01626   0.00938  -0.0750   0.3142   1.0000
   7.750   1.1538   0.01757   0.01033  -0.0719   0.2511   1.0000
   8.000   1.1593   0.01896   0.01138  -0.0687   0.1933   1.0000
   8.250   1.1634   0.02041   0.01253  -0.0653   0.1451   1.0000
   8.500   1.1643   0.02185   0.01376  -0.0613   0.1138   1.0000
   8.750   1.1671   0.02334   0.01513  -0.0578   0.0940   1.0000
   9.000   1.1722   0.02480   0.01654  -0.0549   0.0810   1.0000
   9.250   1.1759   0.02645   0.01812  -0.0520   0.0719   1.0000
   9.500   1.1879   0.02756   0.01934  -0.0502   0.0643   1.0000
   9.750   1.1933   0.02925   0.02101  -0.0478   0.0586   1.0000
  10.000   1.2048   0.03048   0.02233  -0.0461   0.0532   1.0000
  10.250   1.2094   0.03246   0.02425  -0.0437   0.0487   1.0000
  10.500   1.2218   0.03370   0.02568  -0.0422   0.0448   1.0000
  10.750   1.2314   0.03526   0.02726  -0.0406   0.0414   1.0000
  11.000   1.2418   0.03729   0.02931  -0.0386   0.0381   1.0000
  11.250   1.2535   0.03874   0.03092  -0.0371   0.0353   1.0000
  11.500   1.2639   0.04030   0.03253  -0.0358   0.0328   1.0000
  11.750   1.2829   0.04273   0.03495  -0.0345   0.0304   1.0000
  12.000   1.2945   0.04452   0.03699  -0.0330   0.0293   1.0000
  12.250   1.3064   0.04664   0.03936  -0.0315   0.0281   1.0000
  12.500   1.3157   0.04884   0.04177  -0.0300   0.0270   1.0000
  12.750   1.3218   0.05099   0.04408  -0.0286   0.0260   1.0000
  13.000   1.3272   0.05316   0.04633  -0.0273   0.0249   1.0000
  13.250   1.3356   0.05653   0.04982  -0.0261   0.0239   1.0000
  13.500   1.3310   0.06100   0.05461  -0.0243   0.0235   1.0000
  13.750   1.3214   0.06444   0.05834  -0.0226   0.0234   1.0000
  14.000   1.3094   0.06830   0.06249  -0.0213   0.0232   1.0000
  14.250   1.2953   0.07261   0.06709  -0.0203   0.0232   1.0000
  14.500   1.2789   0.07734   0.07209  -0.0198   0.0231   1.0000
  14.750   1.2606   0.08250   0.07750  -0.0199   0.0231   1.0000
  15.000   1.2409   0.08810   0.08334  -0.0206   0.0232   1.0000
  15.250   1.2202   0.09419   0.08966  -0.0220   0.0232   1.0000
  15.500   1.1989   0.10087   0.09655  -0.0242   0.0233   1.0000
  15.750   1.1773   0.10812   0.10399  -0.0271   0.0234   1.0000
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