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S2046 (s2046-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 200,000
Max Cl/Cd: 77.9 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2046-il-200000.txt
Download as CSV file: xf-s2046-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2046                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4188   0.09752   0.09380  -0.0278   1.0000   0.0554
  -9.000  -0.4183   0.09404   0.09036  -0.0295   1.0000   0.0571
  -8.750  -0.4271   0.08998   0.08637  -0.0339   1.0000   0.0596
  -8.500  -0.3609   0.07403   0.07073  -0.0378   1.0000   0.0622
  -8.250  -0.3539   0.07128   0.06799  -0.0364   1.0000   0.0633
  -8.000  -0.3537   0.06817   0.06493  -0.0360   1.0000   0.0643
  -7.750  -0.4625   0.07197   0.06867  -0.0441   1.0000   0.0620
  -7.500  -0.4573   0.07019   0.06692  -0.0414   1.0000   0.0629
  -7.250  -0.4583   0.06685   0.06363  -0.0425   1.0000   0.0637
  -7.000  -0.4608   0.06330   0.06008  -0.0439   1.0000   0.0647
  -6.750  -0.4637   0.05959   0.05634  -0.0452   1.0000   0.0659
  -6.500  -0.4646   0.05558   0.05225  -0.0468   1.0000   0.0677
  -6.250  -0.4661   0.03232   0.02727  -0.0593   1.0000   0.0368
  -6.000  -0.4467   0.02873   0.02320  -0.0599   1.0000   0.0368
  -5.750  -0.4248   0.02629   0.02029  -0.0600   1.0000   0.0375
  -5.500  -0.4013   0.02365   0.01723  -0.0601   1.0000   0.0376
  -5.250  -0.3769   0.02159   0.01480  -0.0601   1.0000   0.0377
  -5.000  -0.3523   0.02013   0.01306  -0.0598   1.0000   0.0382
  -4.750  -0.3260   0.01794   0.01068  -0.0600   1.0000   0.0398
  -4.500  -0.2926   0.01693   0.00963  -0.0614   0.9978   0.0427
  -4.250  -0.2542   0.01618   0.00877  -0.0636   0.9945   0.0477
  -4.000  -0.2174   0.01533   0.00795  -0.0657   0.9907   0.0584
  -3.750  -0.1792   0.01449   0.00717  -0.0680   0.9867   0.0832
  -3.500  -0.1391   0.01410   0.00679  -0.0708   0.9833   0.1052
  -3.250  -0.1040   0.01389   0.00660  -0.0726   0.9774   0.1294
  -3.000  -0.0652   0.01343   0.00627  -0.0751   0.9729   0.1573
  -2.750  -0.0238   0.01285   0.00590  -0.0782   0.9696   0.2033
  -2.500   0.0089   0.01193   0.00566  -0.0799   0.9631   0.3439
  -2.250   0.0476   0.01146   0.00576  -0.0822   0.9583   0.5173
  -2.000   0.0851   0.01136   0.00578  -0.0839   0.9524   0.5825
  -1.750   0.1230   0.01126   0.00575  -0.0855   0.9456   0.6264
  -1.500   0.1684   0.01114   0.00564  -0.0885   0.9419   0.6637
  -1.250   0.2010   0.01104   0.00558  -0.0889   0.9332   0.6897
  -1.000   0.2412   0.01086   0.00543  -0.0908   0.9283   0.7143
  -0.750   0.2725   0.01075   0.00534  -0.0910   0.9195   0.7365
  -0.500   0.3079   0.01055   0.00519  -0.0917   0.9136   0.7598
  -0.250   0.3346   0.01044   0.00514  -0.0908   0.9037   0.7851
   0.000   0.3631   0.01028   0.00503  -0.0901   0.8953   0.8115
   0.250   0.3893   0.01008   0.00489  -0.0890   0.8858   0.8336
   0.500   0.4137   0.00991   0.00477  -0.0877   0.8744   0.8554
   0.750   0.4373   0.00969   0.00461  -0.0861   0.8632   0.8787
   1.000   0.4619   0.00943   0.00441  -0.0846   0.8521   0.9100
   1.250   0.4999   0.00912   0.00413  -0.0860   0.8409   1.0000
   1.500   0.5308   0.00910   0.00405  -0.0866   0.8269   1.0000
   1.750   0.5606   0.00910   0.00398  -0.0868   0.8120   1.0000
   2.000   0.5893   0.00911   0.00393  -0.0867   0.7958   1.0000
   2.250   0.6171   0.00915   0.00392  -0.0864   0.7771   1.0000
   2.500   0.6447   0.00919   0.00392  -0.0860   0.7573   1.0000
   2.750   0.6719   0.00926   0.00391  -0.0855   0.7354   1.0000
   3.000   0.6986   0.00935   0.00391  -0.0849   0.7097   1.0000
   3.250   0.7246   0.00948   0.00395  -0.0841   0.6787   1.0000
   3.500   0.7498   0.00966   0.00399  -0.0832   0.6392   1.0000
   3.750   0.7743   0.00994   0.00407  -0.0822   0.5942   1.0000
   4.000   0.7983   0.01031   0.00421  -0.0813   0.5475   1.0000
   4.250   0.8220   0.01075   0.00444  -0.0804   0.5010   1.0000
   4.500   0.8455   0.01123   0.00471  -0.0795   0.4590   1.0000
   4.750   0.8694   0.01171   0.00503  -0.0788   0.4209   1.0000
   5.000   0.8931   0.01221   0.00537  -0.0781   0.3863   1.0000
   5.250   0.9170   0.01270   0.00575  -0.0774   0.3520   1.0000
   5.500   0.9407   0.01320   0.00614  -0.0768   0.3179   1.0000
   5.750   0.9638   0.01376   0.00655  -0.0761   0.2813   1.0000
   6.000   0.9863   0.01439   0.00701  -0.0753   0.2370   1.0000
   6.250   1.0071   0.01527   0.00759  -0.0743   0.1831   1.0000
   6.500   1.0266   0.01638   0.00842  -0.0732   0.1378   1.0000
   6.750   1.0461   0.01749   0.00932  -0.0721   0.1139   1.0000
   7.000   1.0662   0.01854   0.01028  -0.0710   0.0997   1.0000
   7.250   1.0879   0.01939   0.01116  -0.0700   0.0904   1.0000
   7.500   1.1082   0.02049   0.01229  -0.0689   0.0833   1.0000
   7.750   1.1293   0.02141   0.01322  -0.0679   0.0770   1.0000
   8.000   1.1495   0.02276   0.01457  -0.0668   0.0722   1.0000
   8.250   1.1715   0.02374   0.01566  -0.0659   0.0681   1.0000
   8.500   1.1926   0.02487   0.01678  -0.0651   0.0641   1.0000
   8.750   1.2140   0.02663   0.01861  -0.0643   0.0605   1.0000
   9.000   1.2358   0.02777   0.01994  -0.0633   0.0576   1.0000
   9.250   1.2565   0.02892   0.02119  -0.0624   0.0544   1.0000
   9.500   1.2769   0.03070   0.02296  -0.0618   0.0511   1.0000
   9.750   1.2958   0.03267   0.02519  -0.0607   0.0486   1.0000
  10.000   1.3133   0.03388   0.02664  -0.0593   0.0458   1.0000
  10.250   1.3298   0.03505   0.02795  -0.0580   0.0430   1.0000
  10.500   1.3463   0.03730   0.03021  -0.0572   0.0404   1.0000
  10.750   1.3559   0.03972   0.03300  -0.0552   0.0384   1.0000
  11.000   1.3650   0.04140   0.03498  -0.0531   0.0363   1.0000
  11.250   1.3730   0.04339   0.03720  -0.0511   0.0346   1.0000
  11.500   1.3787   0.04525   0.03923  -0.0490   0.0331   1.0000
  11.750   1.3826   0.04728   0.04134  -0.0468   0.0320   1.0000
  12.000   1.3763   0.05154   0.04582  -0.0444   0.0309   1.0000
  12.250   1.3580   0.05568   0.05029  -0.0411   0.0305   1.0000
  12.500   1.3434   0.05842   0.05332  -0.0387   0.0301   1.0000
  12.750   1.3266   0.06202   0.05719  -0.0373   0.0298   1.0000
  13.000   1.3075   0.06644   0.06189  -0.0370   0.0295   1.0000
  13.250   1.2861   0.07179   0.06750  -0.0379   0.0295   1.0000
  13.500   1.2629   0.07801   0.07396  -0.0401   0.0295   1.0000
  13.750   1.2376   0.08532   0.08149  -0.0436   0.0296   1.0000
  14.000   1.2106   0.09384   0.09021  -0.0486   0.0299   1.0000
  14.250   1.1818   0.10380   0.10032  -0.0548   0.0303   1.0000
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