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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 100,000
Max Cl/Cd: 57.66 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9037-il-100000-n5.txt
Download as CSV file: xf-s9037-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3341   0.09143   0.08670  -0.0335   1.0000   0.0457
  -7.750  -0.3362   0.08870   0.08406  -0.0336   1.0000   0.0452
  -7.500  -0.3417   0.08614   0.08159  -0.0332   1.0000   0.0446
  -7.000  -0.3712   0.07869   0.07434  -0.0341   1.0000   0.0269
  -6.750  -0.3777   0.07638   0.07209  -0.0327   1.0000   0.0261
  -6.500  -0.3845   0.07379   0.06956  -0.0321   1.0000   0.0253
  -6.250  -0.3717   0.06884   0.06459  -0.0375   0.9954   0.0240
  -6.000  -0.3372   0.05621   0.05158  -0.0532   0.9856   0.0200
  -5.750  -0.3135   0.05127   0.04648  -0.0581   0.9785   0.0196
  -5.500  -0.2851   0.04576   0.04069  -0.0636   0.9719   0.0191
  -5.250  -0.2581   0.04072   0.03527  -0.0675   0.9644   0.0187
  -5.000  -0.2263   0.03566   0.02966  -0.0714   0.9585   0.0185
  -4.750  -0.1965   0.03159   0.02500  -0.0735   0.9517   0.0184
  -4.500  -0.1636   0.02817   0.02091  -0.0754   0.9460   0.0186
  -4.250  -0.1259   0.02562   0.01768  -0.0775   0.9423   0.0199
  -4.000  -0.0988   0.02390   0.01576  -0.0779   0.9344   0.0220
  -3.750  -0.0636   0.02232   0.01389  -0.0794   0.9297   0.0243
  -3.500  -0.0335   0.02084   0.01214  -0.0795   0.9226   0.0260
  -3.250  -0.0006   0.01944   0.01052  -0.0801   0.9168   0.0287
  -3.000   0.0299   0.01858   0.00962  -0.0807   0.9097   0.0358
  -2.750   0.0612   0.01765   0.00862  -0.0812   0.9026   0.0482
  -2.500   0.0907   0.01677   0.00778  -0.0813   0.8948   0.0766
  -2.250   0.1212   0.01585   0.00718  -0.0819   0.8875   0.1482
  -2.000   0.1481   0.01514   0.00687  -0.0818   0.8783   0.2602
  -1.750   0.1781   0.01436   0.00660  -0.0822   0.8715   0.4181
  -1.500   0.1999   0.01365   0.00650  -0.0806   0.8612   0.6038
  -1.250   0.2320   0.01285   0.00635  -0.0795   0.8546   0.8822
  -1.000   0.2828   0.01265   0.00592  -0.0838   0.8464   1.0000
  -0.750   0.3094   0.01266   0.00571  -0.0834   0.8355   1.0000
  -0.500   0.3369   0.01265   0.00549  -0.0830   0.8251   1.0000
  -0.250   0.3647   0.01263   0.00529  -0.0826   0.8148   1.0000
   0.000   0.3904   0.01267   0.00517  -0.0820   0.8026   1.0000
   0.250   0.4165   0.01271   0.00508  -0.0814   0.7905   1.0000
   0.500   0.4429   0.01275   0.00498  -0.0808   0.7784   1.0000
   0.750   0.4694   0.01280   0.00491  -0.0803   0.7661   1.0000
   1.000   0.4959   0.01285   0.00485  -0.0798   0.7534   1.0000
   1.250   0.5223   0.01290   0.00481  -0.0792   0.7401   1.0000
   1.500   0.5486   0.01298   0.00478  -0.0786   0.7261   1.0000
   1.750   0.5747   0.01306   0.00478  -0.0780   0.7116   1.0000
   2.000   0.6007   0.01317   0.00481  -0.0774   0.6966   1.0000
   2.250   0.6266   0.01328   0.00487  -0.0768   0.6811   1.0000
   2.500   0.6524   0.01341   0.00493  -0.0762   0.6655   1.0000
   2.750   0.6782   0.01356   0.00501  -0.0756   0.6495   1.0000
   3.000   0.7039   0.01371   0.00510  -0.0749   0.6329   1.0000
   3.250   0.7294   0.01389   0.00523  -0.0743   0.6157   1.0000
   3.500   0.7544   0.01409   0.00539  -0.0736   0.5967   1.0000
   3.750   0.7793   0.01430   0.00555  -0.0729   0.5776   1.0000
   4.000   0.8042   0.01453   0.00572  -0.0722   0.5587   1.0000
   4.250   0.8287   0.01479   0.00599  -0.0715   0.5390   1.0000
   4.500   0.8531   0.01507   0.00623  -0.0707   0.5194   1.0000
   4.750   0.8772   0.01537   0.00649  -0.0700   0.4991   1.0000
   5.000   0.9009   0.01569   0.00679  -0.0692   0.4775   1.0000
   5.250   0.9243   0.01605   0.00714  -0.0684   0.4562   1.0000
   5.500   0.9474   0.01643   0.00749  -0.0675   0.4348   1.0000
   5.750   0.9703   0.01684   0.00788  -0.0667   0.4140   1.0000
   6.000   0.9929   0.01727   0.00831  -0.0658   0.3927   1.0000
   6.250   1.0151   0.01774   0.00879  -0.0649   0.3721   1.0000
   6.500   1.0368   0.01823   0.00929  -0.0639   0.3504   1.0000
   6.750   1.0579   0.01876   0.00982  -0.0629   0.3288   1.0000
   7.000   1.0785   0.01933   0.01038  -0.0618   0.3064   1.0000
   7.250   1.0987   0.01993   0.01099  -0.0608   0.2844   1.0000
   7.500   1.1181   0.02059   0.01167  -0.0596   0.2636   1.0000
   7.750   1.1373   0.02127   0.01237  -0.0584   0.2432   1.0000
   8.000   1.1558   0.02200   0.01313  -0.0572   0.2238   1.0000
   8.250   1.1732   0.02280   0.01393  -0.0558   0.2050   1.0000
   8.500   1.1905   0.02361   0.01479  -0.0545   0.1867   1.0000
   8.750   1.2062   0.02451   0.01574  -0.0530   0.1693   1.0000
   9.000   1.2206   0.02549   0.01672  -0.0514   0.1527   1.0000
   9.250   1.2343   0.02649   0.01776  -0.0497   0.1377   1.0000
   9.500   1.2471   0.02755   0.01887  -0.0480   0.1240   1.0000
   9.750   1.2574   0.02868   0.02005  -0.0459   0.1123   1.0000
  10.000   1.2669   0.02983   0.02129  -0.0438   0.1010   1.0000
  10.250   1.2754   0.03108   0.02266  -0.0416   0.0914   1.0000
  10.500   1.2812   0.03253   0.02416  -0.0394   0.0836   1.0000
  10.750   1.2867   0.03405   0.02582  -0.0373   0.0758   1.0000
  11.000   1.2919   0.03568   0.02758  -0.0354   0.0686   1.0000
  11.250   1.2934   0.03760   0.02954  -0.0335   0.0630   1.0000
  11.500   1.2971   0.03953   0.03165  -0.0319   0.0572   1.0000
  11.750   1.2972   0.04173   0.03394  -0.0305   0.0522   1.0000
  12.000   1.2977   0.04411   0.03648  -0.0292   0.0475   1.0000
  12.250   1.2973   0.04661   0.03913  -0.0284   0.0428   1.0000
  12.500   1.2921   0.04972   0.04229  -0.0278   0.0397   1.0000
  12.750   1.2915   0.05261   0.04544  -0.0274   0.0356   1.0000
  13.000   1.2866   0.05604   0.04899  -0.0276   0.0323   1.0000
  13.250   1.2778   0.06011   0.05313  -0.0281   0.0302   1.0000
  13.500   1.2732   0.06398   0.05727  -0.0287   0.0276   1.0000
  13.750   1.2655   0.06839   0.06186  -0.0299   0.0255   1.0000
  14.000   1.2566   0.07315   0.06676  -0.0315   0.0242   1.0000
  14.250   1.2449   0.07856   0.07229  -0.0336   0.0230   1.0000
  14.500   1.2333   0.08414   0.07797  -0.0357   0.0222   1.0000
  14.750   1.2237   0.08982   0.08390  -0.0380   0.0212   1.0000
  15.000   1.2127   0.09596   0.09027  -0.0408   0.0203   1.0000
  15.250   1.2015   0.10233   0.09684  -0.0439   0.0196   1.0000
  15.500   1.1895   0.10910   0.10379  -0.0474   0.0191   1.0000
  15.750   1.1769   0.11625   0.11111  -0.0512   0.0186   1.0000
  16.000   1.1642   0.12369   0.11872  -0.0553   0.0183   1.0000
  16.250   1.1512   0.13148   0.12667  -0.0598   0.0180   1.0000
  16.500   1.1368   0.13994   0.13529  -0.0646   0.0181   1.0000
  16.750   1.1197   0.14963   0.14516  -0.0703   0.0184   1.0000
  17.000   1.0970   0.16167   0.15736  -0.0773   0.0193   1.0000
  17.250   1.0718   0.17559   0.17134  -0.0852   0.0203   1.0000
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