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S9000 (9%) (s9000-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S9000 (9%) (s9000-il)
Reynolds number: 200,000
Max Cl/Cd: 66.49 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9000-il-200000-n5.txt
Download as CSV file: xf-s9000-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9000 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4391   0.09161   0.08796  -0.0274   1.0000   0.0108
  -9.000  -0.4391   0.08821   0.08459  -0.0283   1.0000   0.0106
  -8.750  -0.4406   0.08450   0.08093  -0.0296   1.0000   0.0105
  -8.500  -0.4437   0.08067   0.07716  -0.0308   1.0000   0.0103
  -8.250  -0.4492   0.07674   0.07328  -0.0322   1.0000   0.0101
  -8.000  -0.4595   0.07262   0.06925  -0.0334   1.0000   0.0100
  -7.750  -0.4704   0.06832   0.06502  -0.0356   1.0000   0.0099
  -7.500  -0.4774   0.06249   0.05920  -0.0403   1.0000   0.0096
  -7.250  -0.4840   0.05604   0.05267  -0.0436   1.0000   0.0094
  -7.000  -0.4886   0.04966   0.04612  -0.0453   1.0000   0.0091
  -6.750  -0.4910   0.04303   0.03920  -0.0460   1.0000   0.0088
  -6.500  -0.4925   0.03432   0.02979  -0.0461   1.0000   0.0083
  -6.250  -0.4753   0.02867   0.02338  -0.0469   0.9986   0.0080
  -6.000  -0.4436   0.02500   0.01910  -0.0493   0.9951   0.0081
  -5.750  -0.4118   0.02247   0.01612  -0.0509   0.9915   0.0082
  -5.500  -0.3791   0.02056   0.01385  -0.0524   0.9877   0.0086
  -5.250  -0.3450   0.01895   0.01197  -0.0540   0.9844   0.0089
  -5.000  -0.3133   0.01760   0.01038  -0.0549   0.9799   0.0096
  -4.750  -0.2807   0.01645   0.00905  -0.0561   0.9751   0.0104
  -4.500  -0.2458   0.01555   0.00806  -0.0578   0.9714   0.0124
  -4.250  -0.2145   0.01497   0.00739  -0.0585   0.9650   0.0155
  -4.000  -0.1804   0.01404   0.00638  -0.0600   0.9597   0.0195
  -3.750  -0.1470   0.01336   0.00566  -0.0612   0.9538   0.0300
  -3.500  -0.1142   0.01270   0.00507  -0.0623   0.9472   0.0496
  -3.250  -0.0790   0.01209   0.00457  -0.0640   0.9423   0.0842
  -3.000  -0.0480   0.01153   0.00420  -0.0648   0.9342   0.1388
  -2.750  -0.0136   0.01096   0.00389  -0.0664   0.9280   0.2137
  -2.500   0.0181   0.01044   0.00365  -0.0674   0.9187   0.3002
  -2.250   0.0504   0.00994   0.00345  -0.0684   0.9093   0.3937
  -2.000   0.0837   0.00945   0.00325  -0.0696   0.9002   0.4908
  -1.750   0.1137   0.00902   0.00315  -0.0698   0.8887   0.5920
  -1.500   0.1423   0.00875   0.00312  -0.0694   0.8763   0.6817
  -1.250   0.1708   0.00861   0.00305  -0.0690   0.8631   0.7404
  -1.000   0.1986   0.00852   0.00298  -0.0684   0.8487   0.7812
  -0.750   0.2256   0.00847   0.00290  -0.0677   0.8327   0.8140
  -0.500   0.2516   0.00844   0.00283  -0.0667   0.8159   0.8432
  -0.250   0.2764   0.00843   0.00277  -0.0655   0.7983   0.8690
   0.000   0.3017   0.00842   0.00271  -0.0644   0.7807   0.8934
   0.250   0.3284   0.00843   0.00263  -0.0637   0.7625   0.9181
   0.500   0.3585   0.00845   0.00256  -0.0638   0.7434   0.9421
   0.750   0.3933   0.00848   0.00249  -0.0650   0.7216   0.9655
   1.000   0.4302   0.00853   0.00242  -0.0668   0.6987   0.9925
   1.250   0.4572   0.00866   0.00242  -0.0666   0.6761   1.0000
   1.500   0.4825   0.00880   0.00244  -0.0661   0.6544   1.0000
   1.750   0.5080   0.00896   0.00248  -0.0656   0.6322   1.0000
   2.000   0.5334   0.00914   0.00254  -0.0651   0.6090   1.0000
   2.250   0.5587   0.00934   0.00263  -0.0645   0.5844   1.0000
   2.500   0.5839   0.00956   0.00272  -0.0640   0.5583   1.0000
   2.750   0.6092   0.00978   0.00283  -0.0634   0.5324   1.0000
   3.000   0.6345   0.01002   0.00296  -0.0630   0.5077   1.0000
   3.250   0.6597   0.01027   0.00314  -0.0625   0.4836   1.0000
   3.500   0.6849   0.01054   0.00331  -0.0620   0.4593   1.0000
   3.750   0.7100   0.01082   0.00351  -0.0615   0.4340   1.0000
   4.000   0.7349   0.01112   0.00374  -0.0610   0.4081   1.0000
   4.250   0.7595   0.01146   0.00397  -0.0604   0.3804   1.0000
   4.500   0.7840   0.01181   0.00423  -0.0599   0.3535   1.0000
   4.750   0.8085   0.01217   0.00451  -0.0594   0.3288   1.0000
   5.000   0.8331   0.01253   0.00484  -0.0589   0.3048   1.0000
   5.250   0.8574   0.01293   0.00517  -0.0584   0.2815   1.0000
   5.500   0.8816   0.01334   0.00552  -0.0579   0.2594   1.0000
   5.750   0.9056   0.01377   0.00590  -0.0574   0.2355   1.0000
   6.000   0.9292   0.01425   0.00633  -0.0568   0.2116   1.0000
   6.250   0.9525   0.01477   0.00677  -0.0562   0.1892   1.0000
   6.500   0.9761   0.01525   0.00724  -0.0556   0.1691   1.0000
   6.750   0.9992   0.01578   0.00773  -0.0550   0.1509   1.0000
   7.000   1.0222   0.01633   0.00829  -0.0544   0.1356   1.0000
   7.250   1.0448   0.01690   0.00887  -0.0537   0.1212   1.0000
   7.500   1.0670   0.01752   0.00948  -0.0530   0.1068   1.0000
   7.750   1.0888   0.01816   0.01013  -0.0522   0.0933   1.0000
   8.250   1.1310   0.01957   0.01158  -0.0505   0.0708   1.0000
   8.500   1.1517   0.02028   0.01238  -0.0496   0.0616   1.0000
   8.750   1.1714   0.02108   0.01322  -0.0486   0.0539   1.0000
   9.000   1.1904   0.02192   0.01409  -0.0475   0.0468   1.0000
   9.250   1.2096   0.02271   0.01500  -0.0464   0.0410   1.0000
   9.500   1.2257   0.02377   0.01607  -0.0450   0.0353   1.0000
   9.750   1.2436   0.02462   0.01707  -0.0438   0.0310   1.0000
  10.000   1.2577   0.02577   0.01829  -0.0422   0.0271   1.0000
  10.250   1.2710   0.02691   0.01961  -0.0404   0.0240   1.0000
  10.500   1.2838   0.02798   0.02081  -0.0386   0.0210   1.0000
  10.750   1.2900   0.02939   0.02228  -0.0361   0.0189   1.0000
  11.000   1.2963   0.03079   0.02385  -0.0335   0.0175   1.0000
  11.250   1.3020   0.03226   0.02549  -0.0312   0.0162   1.0000
  11.500   1.3075   0.03375   0.02711  -0.0292   0.0149   1.0000
  11.750   1.3101   0.03550   0.02897  -0.0272   0.0138   1.0000
  12.000   1.3070   0.03786   0.03146  -0.0253   0.0129   1.0000
  12.250   1.3076   0.04009   0.03389  -0.0239   0.0122   1.0000
  12.500   1.3062   0.04265   0.03665  -0.0228   0.0116   1.0000
  12.750   1.3045   0.04539   0.03957  -0.0223   0.0109   1.0000
  13.000   1.3023   0.04835   0.04268  -0.0222   0.0102   1.0000
  13.250   1.2974   0.05184   0.04633  -0.0227   0.0098   1.0000
  13.500   1.2901   0.05590   0.05057  -0.0238   0.0093   1.0000
  13.750   1.2783   0.06090   0.05572  -0.0255   0.0090   1.0000
  14.000   1.2669   0.06619   0.06117  -0.0276   0.0088   1.0000
  14.250   1.2573   0.07159   0.06681  -0.0301   0.0085   1.0000
  14.500   1.2452   0.07763   0.07304  -0.0331   0.0084   1.0000
  14.750   1.2315   0.08427   0.07988  -0.0366   0.0082   1.0000
  15.000   1.2168   0.09138   0.08716  -0.0405   0.0082   1.0000
  15.250   1.2012   0.09901   0.09497  -0.0448   0.0081   1.0000
  15.500   1.1855   0.10695   0.10308  -0.0493   0.0081   1.0000
  15.750   1.1694   0.11530   0.11158  -0.0541   0.0081   1.0000
  16.000   1.1527   0.12402   0.12046  -0.0592   0.0082   1.0000
  16.250   1.1364   0.13302   0.12959  -0.0645   0.0082   1.0000
  16.500   1.1204   0.14224   0.13891  -0.0699   0.0083   1.0000
  16.750   1.1041   0.15189   0.14867  -0.0756   0.0084   1.0000
  17.000   1.0882   0.16178   0.15865  -0.0814   0.0086   1.0000
  17.250   1.0708   0.17275   0.16971  -0.0879   0.0087   1.0000
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