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SD7034 (sd7034-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: SD7034 (sd7034-il)
Reynolds number: 200,000
Max Cl/Cd: 76.25 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd7034-il-200000-n5.txt
Download as CSV file: xf-sd7034-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7034                                          
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.3345   0.08867   0.08523  -0.0353   1.0000   0.0163
  -8.750  -0.3355   0.08446   0.08107  -0.0373   1.0000   0.0163
  -8.500  -0.3385   0.08031   0.07699  -0.0394   1.0000   0.0166
  -8.250  -0.3401   0.07466   0.07140  -0.0442   0.9837   0.0171
  -8.000  -0.3352   0.06602   0.06277  -0.0554   0.9559   0.0173
  -7.750  -0.3347   0.05402   0.05066  -0.0713   0.9315   0.0173
  -7.500  -0.3648   0.03207   0.02747  -0.0860   0.9070   0.0172
  -7.250  -0.3549   0.02620   0.02057  -0.0868   0.8963   0.0178
  -7.000  -0.3338   0.02463   0.01881  -0.0866   0.8870   0.0183
  -6.750  -0.3112   0.02331   0.01726  -0.0863   0.8790   0.0190
  -6.500  -0.2882   0.02182   0.01546  -0.0859   0.8706   0.0200
  -6.250  -0.2642   0.02040   0.01362  -0.0854   0.8629   0.0216
  -6.000  -0.2397   0.01951   0.01262  -0.0851   0.8549   0.0230
  -5.750  -0.2145   0.01874   0.01170  -0.0847   0.8475   0.0245
  -5.500  -0.1891   0.01775   0.01045  -0.0842   0.8397   0.0261
  -5.250  -0.1635   0.01697   0.00955  -0.0838   0.8325   0.0279
  -5.000  -0.1372   0.01649   0.00900  -0.0835   0.8245   0.0302
  -4.750  -0.1109   0.01586   0.00816  -0.0830   0.8175   0.0325
  -4.500  -0.0845   0.01531   0.00761  -0.0828   0.8093   0.0352
  -4.250  -0.0579   0.01488   0.00706  -0.0824   0.8023   0.0384
  -4.000  -0.0312   0.01434   0.00646  -0.0822   0.7940   0.0414
  -3.750  -0.0043   0.01399   0.00604  -0.0818   0.7869   0.0460
  -3.500   0.0228   0.01357   0.00558  -0.0816   0.7784   0.0511
  -3.250   0.0499   0.01326   0.00518  -0.0813   0.7713   0.0577
  -3.000   0.0772   0.01293   0.00485  -0.0811   0.7627   0.0669
  -2.750   0.1045   0.01265   0.00453  -0.0809   0.7553   0.0771
  -2.500   0.1320   0.01241   0.00428  -0.0807   0.7467   0.0896
  -2.250   0.1594   0.01219   0.00405  -0.0805   0.7391   0.1065
  -2.000   0.1869   0.01196   0.00385  -0.0804   0.7304   0.1294
  -1.750   0.2142   0.01171   0.00367  -0.0803   0.7225   0.1616
  -1.500   0.2415   0.01143   0.00352  -0.0801   0.7137   0.2091
  -1.250   0.2686   0.01114   0.00342  -0.0800   0.7051   0.2766
  -1.000   0.2954   0.01084   0.00333  -0.0799   0.6964   0.3583
  -0.750   0.3218   0.01053   0.00330  -0.0796   0.6872   0.4557
  -0.500   0.3474   0.01025   0.00326  -0.0790   0.6786   0.5548
  -0.250   0.3718   0.00994   0.00328  -0.0780   0.6687   0.6621
   0.000   0.3933   0.00960   0.00329  -0.0760   0.6597   0.7917
   0.250   0.4334   0.00931   0.00315  -0.0777   0.6495   0.9803
   0.500   0.4626   0.00938   0.00310  -0.0779   0.6390   1.0000
   0.750   0.4898   0.00947   0.00307  -0.0777   0.6290   1.0000
   1.000   0.5171   0.00958   0.00306  -0.0775   0.6186   1.0000
   1.250   0.5444   0.00968   0.00307  -0.0773   0.6076   1.0000
   1.500   0.5717   0.00980   0.00309  -0.0771   0.5970   1.0000
   1.750   0.5987   0.00993   0.00311  -0.0768   0.5862   1.0000
   2.000   0.6259   0.01006   0.00317  -0.0766   0.5743   1.0000
   2.250   0.6530   0.01020   0.00324  -0.0764   0.5626   1.0000
   2.500   0.6800   0.01035   0.00331  -0.0762   0.5507   1.0000
   2.750   0.7068   0.01051   0.00339  -0.0759   0.5388   1.0000
   3.000   0.7335   0.01068   0.00350  -0.0757   0.5261   1.0000
   3.250   0.7603   0.01085   0.00362  -0.0754   0.5133   1.0000
   3.500   0.7869   0.01104   0.00375  -0.0752   0.5006   1.0000
   3.750   0.8133   0.01124   0.00391  -0.0749   0.4877   1.0000
   4.000   0.8395   0.01146   0.00407  -0.0746   0.4747   1.0000
   4.250   0.8656   0.01169   0.00425  -0.0743   0.4612   1.0000
   4.500   0.8914   0.01194   0.00445  -0.0740   0.4476   1.0000
   4.750   0.9171   0.01219   0.00467  -0.0736   0.4336   1.0000
   5.000   0.9427   0.01246   0.00490  -0.0733   0.4193   1.0000
   5.250   0.9680   0.01274   0.00516  -0.0729   0.4052   1.0000
   5.500   0.9930   0.01304   0.00543  -0.0725   0.3908   1.0000
   5.750   1.0179   0.01335   0.00572  -0.0721   0.3764   1.0000
   6.000   1.0424   0.01369   0.00603  -0.0716   0.3621   1.0000
   6.250   1.0666   0.01404   0.00637  -0.0711   0.3475   1.0000
   6.500   1.0906   0.01441   0.00672  -0.0706   0.3333   1.0000
   6.750   1.1141   0.01480   0.00709  -0.0700   0.3190   1.0000
   7.000   1.1373   0.01521   0.00750  -0.0694   0.3049   1.0000
   7.250   1.1600   0.01565   0.00792  -0.0687   0.2905   1.0000
   7.500   1.1822   0.01611   0.00836  -0.0680   0.2760   1.0000
   7.750   1.2039   0.01660   0.00885  -0.0673   0.2614   1.0000
   8.000   1.2250   0.01712   0.00935  -0.0664   0.2467   1.0000
   8.250   1.2455   0.01765   0.00988  -0.0655   0.2324   1.0000
   8.500   1.2654   0.01822   0.01044  -0.0646   0.2184   1.0000
   8.750   1.2845   0.01882   0.01104  -0.0635   0.2046   1.0000
   9.000   1.3026   0.01946   0.01167  -0.0624   0.1910   1.0000
   9.250   1.3198   0.02013   0.01234  -0.0611   0.1781   1.0000
   9.500   1.3357   0.02085   0.01306  -0.0597   0.1649   1.0000
   9.750   1.3503   0.02160   0.01382  -0.0581   0.1524   1.0000
  10.000   1.3622   0.02238   0.01462  -0.0561   0.1401   1.0000
  10.250   1.3728   0.02326   0.01550  -0.0541   0.1283   1.0000
  10.500   1.3826   0.02423   0.01648  -0.0521   0.1174   1.0000
  10.750   1.3912   0.02532   0.01758  -0.0502   0.1071   1.0000
  11.000   1.3986   0.02655   0.01881  -0.0484   0.0978   1.0000
  11.250   1.4058   0.02785   0.02015  -0.0467   0.0887   1.0000
  11.500   1.4130   0.02922   0.02157  -0.0452   0.0810   1.0000
  11.750   1.4178   0.03083   0.02320  -0.0437   0.0744   1.0000
  12.000   1.4239   0.03243   0.02486  -0.0424   0.0683   1.0000
  12.250   1.4274   0.03430   0.02678  -0.0412   0.0632   1.0000
  12.500   1.4321   0.03615   0.02872  -0.0402   0.0585   1.0000
  12.750   1.4334   0.03840   0.03103  -0.0393   0.0548   1.0000
  13.000   1.4367   0.04053   0.03327  -0.0386   0.0513   1.0000
  13.250   1.4382   0.04293   0.03575  -0.0380   0.0479   1.0000
  13.500   1.4362   0.04579   0.03867  -0.0376   0.0454   1.0000
  13.750   1.4373   0.04839   0.04141  -0.0374   0.0431   1.0000
  14.000   1.4374   0.05123   0.04437  -0.0373   0.0408   1.0000
  14.250   1.4347   0.05447   0.04772  -0.0375   0.0390   1.0000
  14.500   1.4292   0.05821   0.05153  -0.0380   0.0374   1.0000
  14.750   1.4266   0.06173   0.05518  -0.0385   0.0359   1.0000
  15.000   1.4240   0.06535   0.05897  -0.0392   0.0345   1.0000
  15.250   1.4205   0.06924   0.06298  -0.0401   0.0331   1.0000
  15.500   1.4148   0.07356   0.06742  -0.0414   0.0319   1.0000
  15.750   1.4074   0.07827   0.07223  -0.0429   0.0308   1.0000
  16.000   1.3993   0.08321   0.07725  -0.0446   0.0299   1.0000
  16.250   1.3953   0.08764   0.08185  -0.0462   0.0289   1.0000
  16.500   1.3899   0.09236   0.08672  -0.0479   0.0279   1.0000
  16.750   1.3839   0.09730   0.09179  -0.0499   0.0270   1.0000
  17.000   1.3774   0.10241   0.09702  -0.0521   0.0262   1.0000
  17.250   1.3702   0.10774   0.10246  -0.0545   0.0255   1.0000
  17.500   1.3624   0.11320   0.10801  -0.0570   0.0249   1.0000
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