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S3010-103-84 (s3010-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 100,000
Max Cl/Cd: 52.82 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3010-il-100000-n5.txt
Download as CSV file: xf-s3010-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4217   0.09114   0.08620  -0.0221   1.0000   0.0323
  -8.750  -0.4207   0.08698   0.08209  -0.0243   1.0000   0.0318
  -8.500  -0.4213   0.08263   0.07780  -0.0266   1.0000   0.0310
  -8.250  -0.4251   0.07771   0.07297  -0.0297   1.0000   0.0303
  -8.000  -0.4636   0.06102   0.05623  -0.0459   1.0000   0.0273
  -7.750  -0.4658   0.05625   0.05137  -0.0487   1.0000   0.0271
  -7.500  -0.4660   0.05186   0.04682  -0.0504   1.0000   0.0269
  -7.250  -0.4663   0.04748   0.04223  -0.0513   1.0000   0.0267
  -7.000  -0.4655   0.04369   0.03819  -0.0509   1.0000   0.0265
  -6.750  -0.4635   0.04036   0.03456  -0.0498   1.0000   0.0264
  -6.500  -0.4548   0.03694   0.03074  -0.0493   0.9978   0.0264
  -6.250  -0.4239   0.03280   0.02598  -0.0526   0.9876   0.0264
  -6.000  -0.3908   0.02952   0.02211  -0.0551   0.9789   0.0267
  -5.750  -0.3548   0.02684   0.01888  -0.0575   0.9718   0.0271
  -5.500  -0.3219   0.02492   0.01672  -0.0591   0.9625   0.0282
  -5.250  -0.2875   0.02364   0.01529  -0.0609   0.9540   0.0300
  -5.000  -0.2532   0.02235   0.01378  -0.0623   0.9451   0.0322
  -4.750  -0.2215   0.02108   0.01228  -0.0629   0.9347   0.0336
  -4.500  -0.1901   0.01991   0.01107  -0.0637   0.9250   0.0352
  -4.250  -0.1597   0.01902   0.01012  -0.0641   0.9146   0.0379
  -4.000  -0.1315   0.01828   0.00923  -0.0640   0.9027   0.0418
  -3.750  -0.1037   0.01756   0.00849  -0.0639   0.8913   0.0500
  -3.500  -0.0761   0.01675   0.00770  -0.0637   0.8804   0.0660
  -3.250  -0.0498   0.01600   0.00712  -0.0633   0.8687   0.1064
  -3.000  -0.0247   0.01531   0.00683  -0.0630   0.8564   0.1858
  -2.750   0.0007   0.01476   0.00656  -0.0625   0.8446   0.2662
  -2.500   0.0264   0.01432   0.00631  -0.0619   0.8334   0.3384
  -2.250   0.0515   0.01391   0.00613  -0.0611   0.8219   0.4197
  -2.000   0.0760   0.01355   0.00599  -0.0601   0.8094   0.5045
  -1.750   0.1000   0.01325   0.00590  -0.0587   0.7975   0.5871
  -1.500   0.1234   0.01298   0.00580  -0.0570   0.7861   0.6673
  -1.250   0.1462   0.01276   0.00571  -0.0550   0.7747   0.7446
  -1.000   0.1699   0.01259   0.00562  -0.0531   0.7621   0.8192
  -0.750   0.2013   0.01245   0.00547  -0.0528   0.7498   0.8930
  -0.500   0.2457   0.01232   0.00520  -0.0556   0.7373   0.9625
  -0.250   0.2830   0.01229   0.00499  -0.0573   0.7243   1.0000
   0.000   0.3079   0.01236   0.00486  -0.0566   0.7117   1.0000
   0.250   0.3331   0.01245   0.00479  -0.0560   0.6981   1.0000
   0.500   0.3587   0.01254   0.00475  -0.0554   0.6843   1.0000
   0.750   0.3845   0.01265   0.00471  -0.0549   0.6705   1.0000
   1.000   0.4105   0.01276   0.00470  -0.0544   0.6567   1.0000
   1.250   0.4366   0.01289   0.00470  -0.0539   0.6429   1.0000
   1.500   0.4628   0.01302   0.00472  -0.0534   0.6292   1.0000
   1.750   0.4890   0.01317   0.00476  -0.0529   0.6153   1.0000
   2.000   0.5153   0.01332   0.00481  -0.0525   0.6015   1.0000
   2.250   0.5416   0.01349   0.00488  -0.0520   0.5873   1.0000
   2.500   0.5678   0.01367   0.00497  -0.0515   0.5731   1.0000
   2.750   0.5940   0.01385   0.00507  -0.0511   0.5587   1.0000
   3.000   0.6202   0.01405   0.00520  -0.0507   0.5439   1.0000
   3.250   0.6464   0.01427   0.00537  -0.0503   0.5291   1.0000
   3.500   0.6724   0.01449   0.00554  -0.0499   0.5143   1.0000
   3.750   0.6984   0.01473   0.00573  -0.0495   0.4994   1.0000
   4.000   0.7243   0.01498   0.00595  -0.0490   0.4845   1.0000
   4.250   0.7501   0.01525   0.00618  -0.0486   0.4695   1.0000
   4.500   0.7757   0.01553   0.00643  -0.0482   0.4543   1.0000
   4.750   0.8012   0.01583   0.00670  -0.0477   0.4390   1.0000
   5.000   0.8265   0.01614   0.00700  -0.0473   0.4234   1.0000
   5.250   0.8516   0.01647   0.00731  -0.0468   0.4076   1.0000
   5.500   0.8764   0.01682   0.00764  -0.0463   0.3918   1.0000
   5.750   0.9011   0.01719   0.00802  -0.0458   0.3756   1.0000
   6.000   0.9255   0.01758   0.00842  -0.0453   0.3593   1.0000
   6.250   0.9496   0.01799   0.00884  -0.0448   0.3429   1.0000
   6.500   0.9734   0.01843   0.00929  -0.0443   0.3265   1.0000
   6.750   0.9968   0.01889   0.00978  -0.0437   0.3101   1.0000
   7.000   1.0199   0.01939   0.01029  -0.0431   0.2939   1.0000
   7.250   1.0425   0.01993   0.01084  -0.0424   0.2780   1.0000
   7.500   1.0645   0.02050   0.01144  -0.0417   0.2622   1.0000
   7.750   1.0862   0.02111   0.01206  -0.0410   0.2472   1.0000
   8.000   1.1072   0.02176   0.01273  -0.0402   0.2322   1.0000
   8.250   1.1278   0.02244   0.01345  -0.0394   0.2181   1.0000
   8.500   1.1476   0.02317   0.01423  -0.0386   0.2041   1.0000
   8.750   1.1668   0.02394   0.01504  -0.0376   0.1910   1.0000
   9.000   1.1852   0.02476   0.01590  -0.0367   0.1785   1.0000
   9.250   1.2025   0.02563   0.01681  -0.0356   0.1668   1.0000
   9.500   1.2184   0.02658   0.01779  -0.0344   0.1562   1.0000
   9.750   1.2340   0.02753   0.01883  -0.0332   0.1454   1.0000
  10.000   1.2488   0.02853   0.01993  -0.0319   0.1358   1.0000
  10.250   1.2608   0.02966   0.02108  -0.0304   0.1276   1.0000
  10.500   1.2717   0.03078   0.02231  -0.0288   0.1195   1.0000
  10.750   1.2800   0.03201   0.02361  -0.0269   0.1129   1.0000
  11.000   1.2869   0.03333   0.02505  -0.0252   0.1065   1.0000
  11.250   1.2929   0.03483   0.02662  -0.0235   0.1010   1.0000
  11.500   1.2988   0.03639   0.02831  -0.0221   0.0954   1.0000
  11.750   1.3012   0.03826   0.03018  -0.0208   0.0913   1.0000
  12.000   1.3072   0.04008   0.03221  -0.0198   0.0864   1.0000
  12.250   1.3096   0.04215   0.03439  -0.0190   0.0821   1.0000
  12.500   1.3104   0.04449   0.03675  -0.0183   0.0786   1.0000
  12.750   1.3129   0.04686   0.03936  -0.0179   0.0745   1.0000
  13.000   1.3126   0.04951   0.04215  -0.0178   0.0709   1.0000
  13.250   1.3096   0.05251   0.04514  -0.0179   0.0678   1.0000
  13.500   1.3076   0.05572   0.04862  -0.0184   0.0639   1.0000
  13.750   1.3031   0.05925   0.05230  -0.0193   0.0606   1.0000
  14.000   1.2963   0.06316   0.05626  -0.0205   0.0579   1.0000
  14.250   1.2900   0.06736   0.06065  -0.0219   0.0550   1.0000
  14.500   1.2820   0.07192   0.06541  -0.0237   0.0521   1.0000
  14.750   1.2730   0.07681   0.07042  -0.0258   0.0499   1.0000
  15.000   1.2637   0.08184   0.07553  -0.0281   0.0482   1.0000
  15.250   1.2537   0.08733   0.08118  -0.0306   0.0463   1.0000
  15.500   1.2427   0.09326   0.08732  -0.0334   0.0445   1.0000
  15.750   1.2313   0.09940   0.09364  -0.0365   0.0429   1.0000
  16.000   1.2196   0.10579   0.10016  -0.0399   0.0414   1.0000
  16.250   1.2089   0.11209   0.10653  -0.0434   0.0400   1.0000
  16.500   1.1996   0.11816   0.11266  -0.0466   0.0388   1.0000
  16.750   1.1837   0.12613   0.12086  -0.0510   0.0378   1.0000
  17.000   1.1665   0.13471   0.12964  -0.0560   0.0370   1.0000
  17.250   1.1461   0.14445   0.13956  -0.0617   0.0363   1.0000
  17.500   1.1161   0.15735   0.15264  -0.0695   0.0362   1.0000
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