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SD7062 (14%) (sd7062-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SD7062 (14%) (sd7062-il)
Reynolds number: 200,000
Max Cl/Cd: 70.04 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sd7062-il-200000.txt
Download as CSV file: xf-sd7062-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD7062 (14%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.1905   0.08919   0.08618  -0.0444   0.9909   0.0697
  -9.000  -0.1772   0.08453   0.08152  -0.0484   0.9860   0.0722
  -8.750  -0.2248   0.07231   0.06932  -0.0676   0.9765   0.0762
  -8.500  -0.2907   0.08857   0.08547  -0.0399   0.9974   0.0698
  -8.250  -0.2727   0.08337   0.08027  -0.0476   0.9892   0.0736
  -8.000  -0.2757   0.07225   0.06918  -0.0665   0.9741   0.0773
  -7.750  -0.2430   0.07037   0.06729  -0.0669   0.9710   0.0788
  -7.500  -0.2212   0.06606   0.06297  -0.0732   0.9604   0.0815
  -7.250  -0.2806   0.03690   0.03173  -0.1006   0.9280   0.0500
  -7.000  -0.2520   0.03534   0.03054  -0.1015   0.9201   0.0526
  -6.750  -0.2438   0.02832   0.02200  -0.1006   0.9078   0.0435
  -6.500  -0.2228   0.02621   0.01965  -0.0997   0.8964   0.0432
  -6.250  -0.1984   0.02461   0.01769  -0.0991   0.8875   0.0435
  -6.000  -0.1760   0.02282   0.01580  -0.0984   0.8765   0.0445
  -5.750  -0.1513   0.02174   0.01463  -0.0977   0.8670   0.0455
  -5.500  -0.1264   0.02063   0.01337  -0.0969   0.8569   0.0461
  -5.250  -0.1014   0.01964   0.01223  -0.0960   0.8470   0.0469
  -5.000  -0.0757   0.01873   0.01118  -0.0952   0.8376   0.0479
  -4.750  -0.0505   0.01798   0.01032  -0.0943   0.8273   0.0491
  -4.500  -0.0249   0.01714   0.00939  -0.0935   0.8186   0.0508
  -4.250  -0.0003   0.01651   0.00883  -0.0928   0.8078   0.0536
  -4.000   0.0264   0.01606   0.00824  -0.0921   0.7996   0.0576
  -3.750   0.0507   0.01537   0.00764  -0.0914   0.7885   0.0624
  -3.500   0.0766   0.01477   0.00701  -0.0908   0.7801   0.0709
  -3.250   0.1016   0.01398   0.00639  -0.0902   0.7695   0.1024
  -3.000   0.1266   0.01316   0.00597  -0.0899   0.7607   0.1942
  -2.750   0.1522   0.01270   0.00577  -0.0895   0.7504   0.2741
  -2.500   0.1783   0.01238   0.00566  -0.0891   0.7410   0.3492
  -2.250   0.2040   0.01208   0.00561  -0.0885   0.7314   0.4328
  -2.000   0.2296   0.01191   0.00563  -0.0878   0.7215   0.5029
  -1.750   0.2561   0.01180   0.00556  -0.0871   0.7123   0.5529
  -1.500   0.2820   0.01172   0.00556  -0.0863   0.7018   0.5948
  -1.250   0.3085   0.01166   0.00549  -0.0855   0.6932   0.6356
  -1.000   0.3338   0.01160   0.00551  -0.0846   0.6822   0.6741
  -0.750   0.3595   0.01155   0.00547  -0.0836   0.6731   0.7108
  -0.500   0.3842   0.01150   0.00547  -0.0825   0.6627   0.7469
  -0.250   0.4084   0.01146   0.00547  -0.0811   0.6530   0.7835
   0.000   0.4316   0.01141   0.00543  -0.0795   0.6433   0.8208
   0.250   0.4536   0.01138   0.00543  -0.0777   0.6332   0.8592
   0.500   0.4771   0.01132   0.00534  -0.0760   0.6242   0.9007
   0.750   0.5113   0.01127   0.00528  -0.0767   0.6128   0.9457
   1.000   0.5609   0.01127   0.00515  -0.0809   0.6016   0.9860
   1.250   0.5935   0.01135   0.00507  -0.0821   0.5909   1.0000
   1.500   0.6182   0.01149   0.00511  -0.0817   0.5802   1.0000
   1.750   0.6448   0.01165   0.00509  -0.0814   0.5707   1.0000
   2.000   0.6706   0.01178   0.00517  -0.0811   0.5595   1.0000
   2.250   0.6972   0.01195   0.00523  -0.0808   0.5493   1.0000
   2.500   0.7238   0.01212   0.00528  -0.0805   0.5392   1.0000
   2.750   0.7500   0.01229   0.00540  -0.0802   0.5283   1.0000
   3.000   0.7768   0.01250   0.00547  -0.0799   0.5187   1.0000
   3.250   0.8028   0.01267   0.00561  -0.0795   0.5077   1.0000
   3.500   0.8291   0.01289   0.00575  -0.0792   0.4976   1.0000
   3.750   0.8554   0.01311   0.00587  -0.0789   0.4876   1.0000
   4.000   0.8811   0.01332   0.00606  -0.0785   0.4769   1.0000
   4.250   0.9073   0.01358   0.00621  -0.0781   0.4674   1.0000
   4.500   0.9327   0.01380   0.00642  -0.0777   0.4568   1.0000
   4.750   0.9583   0.01407   0.00663  -0.0773   0.4469   1.0000
   5.000   0.9838   0.01433   0.00681  -0.0769   0.4372   1.0000
   5.250   1.0087   0.01460   0.00709  -0.0764   0.4269   1.0000
   5.500   1.0342   0.01492   0.00730  -0.0760   0.4179   1.0000
   5.750   1.0584   0.01518   0.00759  -0.0754   0.4074   1.0000
   6.000   1.0831   0.01552   0.00787  -0.0749   0.3983   1.0000
   6.250   1.1073   0.01581   0.00815  -0.0743   0.3886   1.0000
   6.500   1.1312   0.01616   0.00848  -0.0738   0.3792   1.0000
   6.750   1.1552   0.01651   0.00877  -0.0732   0.3703   1.0000
   7.000   1.1783   0.01686   0.00915  -0.0725   0.3607   1.0000
   7.500   1.2239   0.01761   0.00989  -0.0710   0.3428   1.0000
   7.750   1.2468   0.01806   0.01025  -0.0703   0.3346   1.0000
   8.000   1.2680   0.01842   0.01069  -0.0694   0.3256   1.0000
   8.250   1.2900   0.01891   0.01110  -0.0686   0.3176   1.0000
   8.500   1.3102   0.01930   0.01157  -0.0675   0.3089   1.0000
   8.750   1.3313   0.01983   0.01204  -0.0667   0.3013   1.0000
   9.000   1.3502   0.02026   0.01254  -0.0654   0.2929   1.0000
   9.250   1.3702   0.02082   0.01306  -0.0644   0.2855   1.0000
   9.500   1.3875   0.02130   0.01362  -0.0630   0.2776   1.0000
   9.750   1.4065   0.02192   0.01416  -0.0619   0.2706   1.0000
  10.000   1.4212   0.02243   0.01479  -0.0601   0.2630   1.0000
  10.250   1.4385   0.02308   0.01534  -0.0588   0.2564   1.0000
  10.500   1.4491   0.02365   0.01606  -0.0564   0.2496   1.0000
  10.750   1.4620   0.02430   0.01669  -0.0545   0.2432   1.0000
  11.000   1.4742   0.02505   0.01749  -0.0527   0.2367   1.0000
  11.250   1.4845   0.02578   0.01829  -0.0506   0.2304   1.0000
  11.500   1.4985   0.02665   0.01909  -0.0492   0.2244   1.0000
  11.750   1.5056   0.02753   0.02012  -0.0471   0.2182   1.0000
  12.000   1.5161   0.02846   0.02103  -0.0455   0.2126   1.0000
  12.250   1.5254   0.02953   0.02218  -0.0439   0.2069   1.0000
  12.500   1.5322   0.03064   0.02338  -0.0422   0.2012   1.0000
  12.750   1.5449   0.03174   0.02436  -0.0411   0.1956   1.0000
  13.000   1.5480   0.03314   0.02598  -0.0394   0.1905   1.0000
  13.250   1.5540   0.03450   0.02740  -0.0380   0.1854   1.0000
  13.500   1.5641   0.03583   0.02867  -0.0370   0.1803   1.0000
  13.750   1.5658   0.03758   0.03060  -0.0358   0.1755   1.0000
  14.000   1.5701   0.03923   0.03230  -0.0348   0.1707   1.0000
  14.250   1.5785   0.04079   0.03383  -0.0339   0.1660   1.0000
  14.500   1.5783   0.04293   0.03615  -0.0331   0.1616   1.0000
  14.750   1.5808   0.04492   0.03822  -0.0324   0.1573   1.0000
  15.000   1.5895   0.04656   0.03978  -0.0318   0.1528   1.0000
  15.250   1.5859   0.04926   0.04269  -0.0314   0.1490   1.0000
  15.500   1.5861   0.05168   0.04521  -0.0311   0.1449   1.0000
  15.750   1.5930   0.05353   0.04700  -0.0308   0.1408   1.0000
  16.000   1.5897   0.05655   0.05020  -0.0308   0.1373   1.0000
  16.250   1.5866   0.05962   0.05341  -0.0310   0.1336   1.0000
  16.500   1.5871   0.06233   0.05615  -0.0313   0.1300   1.0000
  16.750   1.5912   0.06473   0.05855  -0.0313   0.1263   1.0000
  17.000   1.5832   0.06872   0.06276  -0.0321   0.1231   1.0000
  17.250   1.5801   0.07218   0.06631  -0.0329   0.1197   1.0000
  17.500   1.5843   0.07462   0.06873  -0.0333   0.1163   1.0000
  17.750   1.5796   0.07846   0.07269  -0.0342   0.1133   1.0000
  18.000   1.5701   0.08310   0.07753  -0.0358   0.1103   1.0000
  18.250   1.5663   0.08694   0.08145  -0.0371   0.1073   1.0000
  18.500   1.5757   0.08868   0.08308  -0.0372   0.1038   1.0000
  18.750   1.5626   0.09415   0.08878  -0.0394   0.1015   1.0000
  19.000   1.5500   0.09967   0.09450  -0.0418   0.0990   1.0000
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