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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 200,000
Max Cl/Cd: 74.31 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9037-il-200000-n5.txt
Download as CSV file: xf-s9037-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3339   0.08719   0.08383  -0.0339   1.0000   0.0244
  -7.750  -0.3372   0.08454   0.08125  -0.0338   1.0000   0.0244
  -7.250  -0.3607   0.08072   0.07761  -0.0303   1.0000   0.0245
  -6.750  -0.2531   0.04656   0.04352  -0.0597   0.9681   0.0136
  -6.500  -0.2948   0.05659   0.05329  -0.0639   0.9726   0.0135
  -6.250  -0.2708   0.05054   0.04709  -0.0711   0.9647   0.0130
  -6.000  -0.2440   0.04347   0.03975  -0.0781   0.9576   0.0123
  -5.750  -0.2217   0.03633   0.03219  -0.0824   0.9482   0.0115
  -5.500  -0.1981   0.02725   0.02208  -0.0852   0.9404   0.0104
  -5.250  -0.1728   0.02402   0.01825  -0.0856   0.9325   0.0101
  -5.000  -0.1448   0.02148   0.01522  -0.0861   0.9267   0.0102
  -4.750  -0.1191   0.01957   0.01292  -0.0859   0.9189   0.0103
  -4.500  -0.0902   0.01799   0.01106  -0.0862   0.9134   0.0105
  -4.250  -0.0646   0.01685   0.00972  -0.0857   0.9050   0.0108
  -4.000  -0.0364   0.01582   0.00852  -0.0856   0.8987   0.0113
  -3.750  -0.0105   0.01498   0.00755  -0.0851   0.8899   0.0122
  -3.500   0.0166   0.01421   0.00665  -0.0847   0.8821   0.0134
  -3.250   0.0431   0.01361   0.00595  -0.0843   0.8734   0.0162
  -3.000   0.0697   0.01317   0.00542  -0.0839   0.8642   0.0199
  -2.750   0.0969   0.01253   0.00469  -0.0834   0.8561   0.0271
  -2.500   0.1230   0.01198   0.00423  -0.0830   0.8462   0.0529
  -2.250   0.1493   0.01148   0.00390  -0.0827   0.8367   0.1031
  -2.000   0.1758   0.01103   0.00365  -0.0824   0.8276   0.1726
  -1.750   0.2018   0.01063   0.00346  -0.0821   0.8171   0.2526
  -1.500   0.2275   0.01022   0.00332  -0.0817   0.8064   0.3518
  -1.250   0.2525   0.00978   0.00320  -0.0811   0.7958   0.4679
  -1.000   0.2757   0.00928   0.00313  -0.0800   0.7852   0.6139
  -0.500   0.3365   0.00850   0.00297  -0.0793   0.7628   0.9534
  -0.250   0.3754   0.00848   0.00279  -0.0815   0.7509   1.0000
   0.000   0.4011   0.00855   0.00271  -0.0809   0.7384   1.0000
   0.250   0.4270   0.00862   0.00264  -0.0803   0.7252   1.0000
   0.500   0.4529   0.00870   0.00259  -0.0798   0.7114   1.0000
   0.750   0.4788   0.00880   0.00255  -0.0793   0.6971   1.0000
   1.000   0.5047   0.00890   0.00254  -0.0788   0.6824   1.0000
   1.250   0.5307   0.00901   0.00254  -0.0783   0.6677   1.0000
   1.500   0.5567   0.00913   0.00256  -0.0778   0.6527   1.0000
   1.750   0.5827   0.00927   0.00260  -0.0773   0.6374   1.0000
   2.000   0.6086   0.00941   0.00265  -0.0768   0.6217   1.0000
   2.250   0.6344   0.00957   0.00272  -0.0764   0.6050   1.0000
   2.500   0.6599   0.00974   0.00279  -0.0758   0.5873   1.0000
   2.750   0.6854   0.00992   0.00289  -0.0753   0.5680   1.0000
   3.000   0.7108   0.01012   0.00300  -0.0748   0.5492   1.0000
   3.250   0.7361   0.01033   0.00314  -0.0743   0.5313   1.0000
   3.500   0.7614   0.01055   0.00329  -0.0738   0.5130   1.0000
   3.750   0.7865   0.01078   0.00346  -0.0733   0.4937   1.0000
   4.000   0.8112   0.01105   0.00364  -0.0727   0.4730   1.0000
   4.250   0.8358   0.01132   0.00387  -0.0721   0.4518   1.0000
   4.750   0.8846   0.01191   0.00434  -0.0709   0.4122   1.0000
   5.000   0.9088   0.01223   0.00461  -0.0704   0.3927   1.0000
   5.250   0.9328   0.01257   0.00492  -0.0697   0.3738   1.0000
   5.500   0.9568   0.01291   0.00523  -0.0691   0.3543   1.0000
   5.750   0.9802   0.01329   0.00556  -0.0685   0.3343   1.0000
   6.000   1.0033   0.01369   0.00592  -0.0678   0.3127   1.0000
   6.250   1.0259   0.01413   0.00632  -0.0670   0.2910   1.0000
   6.500   1.0486   0.01457   0.00673  -0.0663   0.2707   1.0000
   6.750   1.0709   0.01503   0.00717  -0.0655   0.2515   1.0000
   7.000   1.0928   0.01553   0.00764  -0.0647   0.2330   1.0000
   7.250   1.1145   0.01604   0.00815  -0.0639   0.2138   1.0000
   7.500   1.1357   0.01658   0.00868  -0.0630   0.1960   1.0000
   7.750   1.1560   0.01719   0.00926  -0.0620   0.1778   1.0000
   8.000   1.1761   0.01781   0.00986  -0.0610   0.1591   1.0000
   8.250   1.1956   0.01846   0.01049  -0.0600   0.1424   1.0000
   8.500   1.2145   0.01915   0.01119  -0.0588   0.1275   1.0000
   8.750   1.2327   0.01987   0.01191  -0.0576   0.1137   1.0000
   9.000   1.2506   0.02059   0.01267  -0.0564   0.1017   1.0000
   9.250   1.2677   0.02134   0.01346  -0.0550   0.0909   1.0000
   9.500   1.2837   0.02215   0.01431  -0.0535   0.0804   1.0000
   9.750   1.2980   0.02302   0.01521  -0.0518   0.0710   1.0000
  10.000   1.3093   0.02396   0.01617  -0.0497   0.0629   1.0000
  10.250   1.3213   0.02485   0.01718  -0.0477   0.0556   1.0000
  10.500   1.3308   0.02591   0.01828  -0.0455   0.0483   1.0000
  10.750   1.3391   0.02708   0.01944  -0.0434   0.0405   1.0000
  11.000   1.3491   0.02816   0.02059  -0.0416   0.0335   1.0000
  11.250   1.3564   0.02947   0.02194  -0.0397   0.0280   1.0000
  11.500   1.3627   0.03090   0.02344  -0.0379   0.0239   1.0000
  11.750   1.3679   0.03246   0.02511  -0.0361   0.0206   1.0000
  12.000   1.3720   0.03419   0.02695  -0.0345   0.0173   1.0000
  12.250   1.3731   0.03628   0.02913  -0.0329   0.0149   1.0000
  12.500   1.3748   0.03840   0.03143  -0.0316   0.0131   1.0000
  12.750   1.3735   0.04093   0.03407  -0.0305   0.0115   1.0000
  13.000   1.3689   0.04396   0.03726  -0.0297   0.0104   1.0000
  13.250   1.3659   0.04696   0.04045  -0.0292   0.0098   1.0000
  13.500   1.3614   0.05030   0.04397  -0.0291   0.0091   1.0000
  13.750   1.3554   0.05401   0.04784  -0.0294   0.0086   1.0000
  14.000   1.3495   0.05791   0.05191  -0.0300   0.0083   1.0000
  14.250   1.3409   0.06237   0.05652  -0.0311   0.0079   1.0000
  14.500   1.3313   0.06721   0.06153  -0.0327   0.0077   1.0000
  14.750   1.3191   0.07275   0.06722  -0.0347   0.0074   1.0000
  15.000   1.3056   0.07876   0.07340  -0.0372   0.0073   1.0000
  15.250   1.2946   0.08462   0.07942  -0.0398   0.0072   1.0000
  15.500   1.2844   0.09058   0.08556  -0.0425   0.0070   1.0000
  15.750   1.2713   0.09722   0.09237  -0.0457   0.0070   1.0000
  16.000   1.2602   0.10376   0.09908  -0.0490   0.0068   1.0000
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