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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.2 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9037-il-1000000.txt
Download as CSV file: xf-s9037-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2622   0.08282   0.08135  -0.0346   1.0000   0.0093
  -8.750  -0.2647   0.07858   0.07714  -0.0358   1.0000   0.0098
  -8.500  -0.2662   0.07502   0.07360  -0.0362   0.9997   0.0099
  -8.250  -0.2594   0.06995   0.06854  -0.0397   0.9960   0.0099
  -8.000  -0.2528   0.06489   0.06348  -0.0434   0.9906   0.0100
  -7.750  -0.2449   0.05949   0.05808  -0.0479   0.9862   0.0100
  -7.500  -0.2366   0.05382   0.05241  -0.0533   0.9790   0.0100
  -7.250  -0.2470   0.04523   0.04381  -0.0619   0.9594   0.0103
  -7.000  -0.2480   0.03980   0.03831  -0.0673   0.9417   0.0104
  -6.750  -0.2454   0.03515   0.03358  -0.0707   0.9276   0.0105
  -6.500  -0.2379   0.03102   0.02933  -0.0733   0.9159   0.0107
  -6.250  -0.2282   0.02642   0.02459  -0.0758   0.9054   0.0109
  -6.000  -0.2149   0.02265   0.02066  -0.0773   0.8963   0.0113
  -5.750  -0.2000   0.01875   0.01655  -0.0786   0.8873   0.0117
  -5.500  -0.1826   0.01487   0.01241  -0.0795   0.8790   0.0126
  -5.250  -0.1613   0.01184   0.00904  -0.0796   0.8717   0.0137
  -5.000  -0.1371   0.01048   0.00734  -0.0794   0.8634   0.0142
  -4.250  -0.0657   0.01259   0.00787  -0.0833   0.8582   0.0092
  -4.000  -0.0403   0.01042   0.00535  -0.0824   0.8495   0.0078
  -3.750  -0.0139   0.00955   0.00430  -0.0819   0.8408   0.0074
  -3.500   0.0130   0.00900   0.00365  -0.0815   0.8313   0.0073
  -3.250   0.0401   0.00852   0.00306  -0.0812   0.8217   0.0073
  -3.000   0.0674   0.00813   0.00257  -0.0809   0.8124   0.0074
  -2.750   0.0949   0.00782   0.00217  -0.0807   0.8024   0.0078
  -2.500   0.1226   0.00758   0.00187  -0.0805   0.7924   0.0086
  -2.250   0.1504   0.00733   0.00154  -0.0803   0.7825   0.0140
  -2.000   0.1775   0.00699   0.00134  -0.0801   0.7721   0.0562
  -1.750   0.2051   0.00679   0.00124  -0.0801   0.7606   0.0942
  -1.500   0.2323   0.00654   0.00115  -0.0800   0.7486   0.1578
  -1.250   0.2591   0.00621   0.00109  -0.0799   0.7362   0.2600
  -1.000   0.2860   0.00593   0.00105  -0.0799   0.7238   0.3585
  -0.750   0.3130   0.00569   0.00102  -0.0798   0.7115   0.4545
  -0.500   0.3392   0.00536   0.00102  -0.0796   0.6990   0.5896
  -0.250   0.3648   0.00507   0.00104  -0.0791   0.6864   0.7159
   0.000   0.3876   0.00475   0.00108  -0.0778   0.6739   0.8549
   0.250   0.4132   0.00461   0.00110  -0.0767   0.6608   0.9658
   0.500   0.4569   0.00466   0.00106  -0.0802   0.6457   0.9982
   0.750   0.4847   0.00476   0.00106  -0.0801   0.6296   1.0000
   1.000   0.5109   0.00486   0.00108  -0.0797   0.6128   1.0000
   1.250   0.5373   0.00497   0.00110  -0.0794   0.5967   1.0000
   1.500   0.5639   0.00508   0.00113  -0.0791   0.5806   1.0000
   1.750   0.5905   0.00520   0.00117  -0.0788   0.5651   1.0000
   2.000   0.6171   0.00534   0.00123  -0.0785   0.5481   1.0000
   2.250   0.6435   0.00549   0.00129  -0.0783   0.5291   1.0000
   2.500   0.6701   0.00565   0.00136  -0.0780   0.5087   1.0000
   3.000   0.7230   0.00599   0.00154  -0.0775   0.4701   1.0000
   3.250   0.7496   0.00616   0.00163  -0.0773   0.4518   1.0000
   3.500   0.7759   0.00635   0.00174  -0.0770   0.4331   1.0000
   3.750   0.8023   0.00654   0.00186  -0.0768   0.4153   1.0000
   4.000   0.8288   0.00673   0.00198  -0.0766   0.3985   1.0000
   4.250   0.8550   0.00694   0.00213  -0.0763   0.3786   1.0000
   4.500   0.8807   0.00720   0.00228  -0.0760   0.3557   1.0000
   4.750   0.9066   0.00744   0.00245  -0.0757   0.3351   1.0000
   5.000   0.9324   0.00769   0.00263  -0.0754   0.3179   1.0000
   5.250   0.9583   0.00792   0.00281  -0.0752   0.2996   1.0000
   5.500   0.9837   0.00821   0.00301  -0.0748   0.2789   1.0000
   5.750   1.0091   0.00849   0.00322  -0.0745   0.2613   1.0000
   6.000   1.0345   0.00876   0.00345  -0.0742   0.2447   1.0000
   6.250   1.0592   0.00911   0.00370  -0.0738   0.2228   1.0000
   6.500   1.0835   0.00948   0.00398  -0.0733   0.2001   1.0000
   6.750   1.1077   0.00986   0.00427  -0.0728   0.1804   1.0000
   7.000   1.1319   0.01023   0.00458  -0.0724   0.1631   1.0000
   7.250   1.1558   0.01061   0.00490  -0.0719   0.1456   1.0000
   7.500   1.1790   0.01107   0.00525  -0.0712   0.1266   1.0000
   7.750   1.2022   0.01150   0.00562  -0.0706   0.1113   1.0000
   8.000   1.2254   0.01192   0.00599  -0.0700   0.0982   1.0000
   8.250   1.2482   0.01237   0.00640  -0.0694   0.0852   1.0000
   8.500   1.2703   0.01287   0.00683  -0.0687   0.0712   1.0000
   8.750   1.2920   0.01338   0.00729  -0.0679   0.0597   1.0000
   9.000   1.3134   0.01390   0.00777  -0.0670   0.0500   1.0000
   9.250   1.3340   0.01447   0.00829  -0.0661   0.0401   1.0000
   9.500   1.3542   0.01505   0.00883  -0.0651   0.0320   1.0000
   9.750   1.3747   0.01558   0.00937  -0.0641   0.0267   1.0000
  10.000   1.3939   0.01618   0.00996  -0.0630   0.0212   1.0000
  10.250   1.4113   0.01689   0.01065  -0.0616   0.0147   1.0000
  10.500   1.4242   0.01792   0.01162  -0.0596   0.0068   1.0000
  10.750   1.4375   0.01885   0.01259  -0.0575   0.0048   1.0000
  11.000   1.4518   0.01950   0.01331  -0.0555   0.0044   1.0000
  11.250   1.4634   0.02021   0.01410  -0.0532   0.0040   1.0000
  11.500   1.4741   0.02099   0.01495  -0.0508   0.0037   1.0000
  11.750   1.4830   0.02190   0.01595  -0.0483   0.0035   1.0000
  12.000   1.4851   0.02331   0.01749  -0.0451   0.0030   1.0000
  12.250   1.4898   0.02459   0.01889  -0.0426   0.0030   1.0000
  12.500   1.4957   0.02584   0.02024  -0.0404   0.0029   1.0000
  12.750   1.5013   0.02717   0.02168  -0.0384   0.0028   1.0000
  13.000   1.5052   0.02872   0.02333  -0.0364   0.0027   1.0000
  13.250   1.5081   0.03042   0.02515  -0.0346   0.0027   1.0000
  13.500   1.5088   0.03242   0.02726  -0.0330   0.0026   1.0000
  13.750   1.5079   0.03469   0.02965  -0.0316   0.0025   1.0000
  14.000   1.5091   0.03689   0.03195  -0.0306   0.0024   1.0000
  14.250   1.5052   0.03975   0.03495  -0.0298   0.0024   1.0000
  14.500   1.5036   0.04253   0.03784  -0.0294   0.0024   1.0000
  14.750   1.4986   0.04589   0.04132  -0.0293   0.0023   1.0000
  15.000   1.4938   0.04941   0.04497  -0.0296   0.0022   1.0000
  15.250   1.4894   0.05306   0.04874  -0.0302   0.0022   1.0000
  15.500   1.4804   0.05758   0.05339  -0.0313   0.0021   1.0000
  15.750   1.4707   0.06247   0.05843  -0.0329   0.0022   1.0000
  16.000   1.4554   0.06852   0.06463  -0.0351   0.0021   1.0000
  16.250   1.4464   0.07382   0.07004  -0.0373   0.0021   1.0000
  16.500   1.4327   0.08017   0.07653  -0.0402   0.0021   1.0000
  16.750   1.4168   0.08716   0.08366  -0.0435   0.0021   1.0000
  17.000   1.4004   0.09451   0.09116  -0.0471   0.0021   1.0000
  17.250   1.3832   0.10219   0.09897  -0.0510   0.0021   1.0000
  17.500   1.3691   0.10949   0.10640  -0.0548   0.0021   1.0000
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