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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 200,000
Max Cl/Cd: 78.14 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9037-il-200000.txt
Download as CSV file: xf-s9037-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3616   0.08900   0.08585  -0.0375   1.0000   0.0381
  -7.500  -0.3716   0.08676   0.08368  -0.0374   1.0000   0.0382
  -7.250  -0.3815   0.08449   0.08146  -0.0371   1.0000   0.0382
  -7.000  -0.3949   0.08068   0.07771  -0.0365   1.0000   0.0385
  -6.750  -0.4031   0.07764   0.07475  -0.0317   1.0000   0.0393
  -6.500  -0.4082   0.07569   0.07283  -0.0290   1.0000   0.0399
  -6.250  -0.3942   0.07260   0.06975  -0.0306   0.9975   0.0411
  -6.000  -0.3653   0.06787   0.06497  -0.0376   0.9924   0.0433
  -5.750  -0.3319   0.06202   0.05901  -0.0474   0.9861   0.0464
  -5.500  -0.2883   0.05243   0.04881  -0.0638   0.9774   0.0509
  -5.250  -0.2632   0.04863   0.04512  -0.0658   0.9734   0.0526
  -5.000  -0.2295   0.04531   0.04173  -0.0699   0.9700   0.0559
  -4.750  -0.1963   0.04005   0.03582  -0.0754   0.9613   0.0646
  -4.500  -0.1626   0.03678   0.03260  -0.0784   0.9580   0.0675
  -4.250  -0.1300   0.03373   0.02902  -0.0812   0.9510   0.0784
  -4.000  -0.0877   0.02413   0.01795  -0.0812   0.9468   0.0284
  -3.750  -0.0477   0.02095   0.01439  -0.0837   0.9441   0.0267
  -3.500  -0.0117   0.01883   0.01188  -0.0849   0.9391   0.0264
  -3.250   0.0236   0.01734   0.01013  -0.0858   0.9332   0.0274
  -3.000   0.0615   0.01566   0.00840  -0.0876   0.9296   0.0316
  -2.750   0.0919   0.01497   0.00765  -0.0876   0.9217   0.0386
  -2.500   0.1253   0.01355   0.00632  -0.0884   0.9162   0.0673
  -2.250   0.1525   0.01240   0.00572  -0.0884   0.9078   0.1900
  -2.000   0.1817   0.01145   0.00544  -0.0888   0.9012   0.3741
  -1.750   0.2031   0.01064   0.00534  -0.0873   0.8914   0.5764
  -1.500   0.2232   0.00976   0.00526  -0.0840   0.8851   0.8407
  -1.250   0.2932   0.00938   0.00479  -0.0918   0.8800   1.0000
  -1.000   0.3192   0.00929   0.00452  -0.0910   0.8712   1.0000
  -0.750   0.3421   0.00929   0.00437  -0.0897   0.8593   1.0000
  -0.500   0.3661   0.00929   0.00422  -0.0886   0.8481   1.0000
  -0.250   0.3910   0.00928   0.00407  -0.0876   0.8373   1.0000
   0.000   0.4165   0.00926   0.00392  -0.0868   0.8268   1.0000
   0.250   0.4418   0.00925   0.00378  -0.0859   0.8152   1.0000
   0.500   0.4669   0.00927   0.00369  -0.0850   0.8024   1.0000
   0.750   0.4922   0.00930   0.00362  -0.0842   0.7895   1.0000
   1.000   0.5178   0.00934   0.00357  -0.0834   0.7763   1.0000
   1.250   0.5435   0.00938   0.00352  -0.0827   0.7629   1.0000
   1.500   0.5694   0.00944   0.00350  -0.0821   0.7492   1.0000
   1.750   0.5953   0.00952   0.00348  -0.0814   0.7350   1.0000
   2.000   0.6212   0.00960   0.00350  -0.0808   0.7203   1.0000
   2.250   0.6470   0.00970   0.00351  -0.0801   0.7047   1.0000
   2.500   0.6728   0.00981   0.00353  -0.0795   0.6885   1.0000
   2.750   0.6984   0.00993   0.00357  -0.0788   0.6716   1.0000
   3.000   0.7238   0.01007   0.00366  -0.0782   0.6535   1.0000
   3.250   0.7493   0.01023   0.00377  -0.0776   0.6357   1.0000
   3.500   0.7748   0.01040   0.00387  -0.0769   0.6179   1.0000
   3.750   0.7999   0.01059   0.00400  -0.0763   0.5986   1.0000
   4.000   0.8248   0.01079   0.00413  -0.0756   0.5778   1.0000
   4.250   0.8496   0.01102   0.00431  -0.0749   0.5573   1.0000
   4.500   0.8741   0.01126   0.00450  -0.0742   0.5359   1.0000
   4.750   0.8985   0.01154   0.00471  -0.0735   0.5155   1.0000
   5.000   0.9228   0.01181   0.00495  -0.0728   0.4937   1.0000
   5.250   0.9467   0.01213   0.00523  -0.0721   0.4727   1.0000
   5.500   0.9704   0.01245   0.00552  -0.0714   0.4504   1.0000
   5.750   0.9936   0.01282   0.00583  -0.0706   0.4280   1.0000
   6.000   1.0164   0.01321   0.00615  -0.0697   0.4045   1.0000
   6.250   1.0391   0.01360   0.00654  -0.0689   0.3807   1.0000
   6.500   1.0613   0.01404   0.00693  -0.0680   0.3580   1.0000
   6.750   1.0832   0.01450   0.00736  -0.0670   0.3351   1.0000
   7.000   1.1048   0.01499   0.00782  -0.0661   0.3118   1.0000
   7.250   1.1255   0.01554   0.00833  -0.0650   0.2889   1.0000
   7.500   1.1461   0.01610   0.00887  -0.0640   0.2657   1.0000
   7.750   1.1658   0.01671   0.00944  -0.0629   0.2424   1.0000
   8.000   1.1843   0.01741   0.01006  -0.0616   0.2201   1.0000
   8.250   1.2036   0.01806   0.01071  -0.0604   0.1979   1.0000
   8.500   1.2205   0.01888   0.01147  -0.0590   0.1788   1.0000
   8.750   1.2383   0.01962   0.01225  -0.0577   0.1595   1.0000
   9.000   1.2544   0.02048   0.01309  -0.0561   0.1424   1.0000
   9.250   1.2688   0.02144   0.01401  -0.0544   0.1270   1.0000
   9.500   1.2815   0.02250   0.01504  -0.0524   0.1126   1.0000
   9.750   1.2930   0.02355   0.01610  -0.0503   0.0998   1.0000
  10.000   1.3032   0.02458   0.01718  -0.0480   0.0886   1.0000
  10.250   1.3123   0.02569   0.01836  -0.0456   0.0786   1.0000
  10.500   1.3193   0.02698   0.01971  -0.0431   0.0698   1.0000
  10.750   1.3236   0.02844   0.02113  -0.0407   0.0617   1.0000
  11.000   1.3341   0.02940   0.02222  -0.0391   0.0534   1.0000
  11.250   1.3403   0.03082   0.02374  -0.0372   0.0463   1.0000
  11.500   1.3410   0.03273   0.02565  -0.0351   0.0408   1.0000
  11.750   1.3467   0.03438   0.02747  -0.0335   0.0346   1.0000
  12.000   1.3400   0.03723   0.03034  -0.0315   0.0299   1.0000
  12.250   1.3408   0.03954   0.03282  -0.0301   0.0253   1.0000
  12.500   1.3336   0.04277   0.03610  -0.0288   0.0231   1.0000
  12.750   1.3287   0.04611   0.03960  -0.0276   0.0212   1.0000
  13.000   1.3274   0.04915   0.04283  -0.0269   0.0195   1.0000
  13.250   1.3258   0.05229   0.04611  -0.0264   0.0185   1.0000
  13.500   1.3230   0.05562   0.04956  -0.0263   0.0175   1.0000
  13.750   1.3183   0.05933   0.05339  -0.0265   0.0166   1.0000
  14.000   1.3114   0.06370   0.05791  -0.0264   0.0159   1.0000
  14.250   1.3042   0.06815   0.06258  -0.0271   0.0154   1.0000
  14.500   1.2982   0.07250   0.06715  -0.0281   0.0151   1.0000
  14.750   1.2906   0.07721   0.07209  -0.0299   0.0145   1.0000
  15.000   1.2812   0.08252   0.07761  -0.0318   0.0143   1.0000
  15.250   1.2708   0.08817   0.08348  -0.0342   0.0141   1.0000
  15.500   1.2587   0.09439   0.08991  -0.0371   0.0139   1.0000
  15.750   1.2450   0.10121   0.09693  -0.0405   0.0139   1.0000
  16.000   1.2301   0.10854   0.10448  -0.0445   0.0139   1.0000
  16.250   1.2141   0.11642   0.11256  -0.0491   0.0139   1.0000
  16.500   1.1971   0.12492   0.12125  -0.0542   0.0140   1.0000
  16.750   1.1792   0.13404   0.13055  -0.0600   0.0142   1.0000
  17.000   1.1600   0.14394   0.14061  -0.0663   0.0144   1.0000
  17.250   1.1393   0.15483   0.15164  -0.0734   0.0148   1.0000
  17.500   1.1161   0.16677   0.16364  -0.0808   0.0155   1.0000
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