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S2046 (s2046-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 1,000,000
Max Cl/Cd: 108.27 at α=4°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2046-il-1000000.txt
Download as CSV file: xf-s2046-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.5977   0.05414   0.05243  -0.0507   1.0000   0.0130
  -9.500  -0.6032   0.04861   0.04683  -0.0559   1.0000   0.0129
  -9.250  -0.6294   0.04154   0.03956  -0.0637   1.0000   0.0129
  -9.000  -0.6602   0.03247   0.03011  -0.0670   0.9994   0.0116
  -8.750  -0.6366   0.02479   0.02170  -0.0745   0.9961   0.0113
  -8.500  -0.6063   0.02129   0.01774  -0.0780   0.9943   0.0113
  -8.250  -0.5762   0.01936   0.01557  -0.0799   0.9921   0.0115
  -8.000  -0.5451   0.01776   0.01374  -0.0816   0.9896   0.0118
  -7.750  -0.5131   0.01622   0.01199  -0.0833   0.9876   0.0120
  -7.500  -0.4798   0.01505   0.01065  -0.0850   0.9859   0.0122
  -7.250  -0.4459   0.01414   0.00961  -0.0866   0.9846   0.0125
  -7.000  -0.4111   0.01351   0.00888  -0.0883   0.9835   0.0127
  -6.750  -0.3805   0.01223   0.00746  -0.0894   0.9805   0.0130
  -6.500  -0.3499   0.01112   0.00623  -0.0904   0.9767   0.0134
  -6.250  -0.3178   0.01044   0.00547  -0.0915   0.9736   0.0138
  -6.000  -0.2852   0.00989   0.00487  -0.0926   0.9707   0.0142
  -5.750  -0.2566   0.00946   0.00440  -0.0928   0.9651   0.0147
  -5.500  -0.2274   0.00907   0.00396  -0.0931   0.9594   0.0152
  -5.250  -0.1981   0.00873   0.00356  -0.0933   0.9540   0.0160
  -5.000  -0.1707   0.00845   0.00324  -0.0931   0.9463   0.0168
  -4.750  -0.1426   0.00810   0.00282  -0.0930   0.9396   0.0181
  -4.500  -0.1153   0.00781   0.00251  -0.0928   0.9313   0.0205
  -4.250  -0.0877   0.00754   0.00223  -0.0926   0.9237   0.0274
  -4.000  -0.0604   0.00725   0.00202  -0.0924   0.9153   0.0493
  -3.750  -0.0330   0.00710   0.00188  -0.0922   0.9060   0.0609
  -3.500  -0.0056   0.00696   0.00175  -0.0919   0.8965   0.0727
  -3.250   0.0220   0.00683   0.00162  -0.0917   0.8863   0.0867
  -3.000   0.0498   0.00668   0.00151  -0.0916   0.8766   0.1020
  -2.750   0.0776   0.00653   0.00139  -0.0915   0.8670   0.1209
  -2.500   0.1054   0.00636   0.00127  -0.0914   0.8569   0.1486
  -2.250   0.1334   0.00616   0.00117  -0.0914   0.8469   0.1891
  -2.000   0.1612   0.00585   0.00107  -0.0915   0.8373   0.2633
  -1.750   0.1889   0.00548   0.00099  -0.0916   0.8274   0.3678
  -1.500   0.2169   0.00528   0.00095  -0.0916   0.8172   0.4377
  -1.250   0.2449   0.00519   0.00094  -0.0915   0.8071   0.4800
  -1.000   0.2728   0.00514   0.00093  -0.0914   0.7964   0.5163
  -0.750   0.3009   0.00510   0.00093  -0.0913   0.7848   0.5467
  -0.500   0.3289   0.00509   0.00093  -0.0911   0.7729   0.5684
  -0.250   0.3569   0.00510   0.00093  -0.0910   0.7602   0.5876
   0.000   0.3848   0.00512   0.00094  -0.0908   0.7470   0.6036
   0.250   0.4127   0.00515   0.00096  -0.0906   0.7328   0.6204
   0.500   0.4405   0.00519   0.00098  -0.0904   0.7174   0.6348
   0.750   0.4680   0.00522   0.00102  -0.0902   0.7005   0.6552
   1.000   0.4955   0.00528   0.00106  -0.0900   0.6816   0.6780
   1.250   0.5227   0.00534   0.00112  -0.0897   0.6607   0.6976
   1.500   0.5497   0.00545   0.00118  -0.0894   0.6350   0.7154
   1.750   0.5765   0.00559   0.00125  -0.0890   0.6042   0.7303
   2.000   0.6026   0.00580   0.00133  -0.0886   0.5622   0.7446
   2.250   0.6281   0.00609   0.00145  -0.0881   0.5086   0.7591
   2.500   0.6538   0.00638   0.00158  -0.0876   0.4618   0.7742
   2.750   0.6797   0.00665   0.00172  -0.0872   0.4211   0.7904
   3.000   0.7058   0.00686   0.00186  -0.0869   0.3905   0.8081
   3.250   0.7319   0.00703   0.00200  -0.0865   0.3640   0.8285
   3.500   0.7572   0.00721   0.00214  -0.0859   0.3360   0.8556
   3.750   0.7787   0.00721   0.00225  -0.0844   0.3105   0.9350
   4.000   0.8077   0.00746   0.00240  -0.0847   0.2837   1.0000
   4.250   0.8346   0.00771   0.00257  -0.0845   0.2610   1.0000
   4.500   0.8611   0.00800   0.00275  -0.0843   0.2372   1.0000
   4.750   0.8872   0.00834   0.00295  -0.0841   0.2098   1.0000
   5.000   0.9128   0.00873   0.00319  -0.0837   0.1780   1.0000
   5.250   0.9381   0.00916   0.00347  -0.0834   0.1464   1.0000
   5.500   0.9631   0.00964   0.00378  -0.0829   0.1166   1.0000
   5.750   0.9882   0.01007   0.00410  -0.0825   0.0939   1.0000
   6.000   1.0133   0.01051   0.00443  -0.0821   0.0765   1.0000
   6.250   1.0388   0.01088   0.00475  -0.0817   0.0658   1.0000
   6.500   1.0646   0.01121   0.00506  -0.0814   0.0586   1.0000
   6.750   1.0896   0.01164   0.00544  -0.0809   0.0512   1.0000
   7.000   1.1154   0.01193   0.00575  -0.0806   0.0479   1.0000
   7.250   1.1406   0.01230   0.00611  -0.0801   0.0439   1.0000
   7.500   1.1647   0.01282   0.00663  -0.0795   0.0395   1.0000
   7.750   1.1905   0.01307   0.00692  -0.0792   0.0381   1.0000
   8.000   1.2156   0.01339   0.00725  -0.0788   0.0357   1.0000
   8.250   1.2396   0.01385   0.00769  -0.0782   0.0326   1.0000
   8.500   1.2630   0.01439   0.00828  -0.0775   0.0304   1.0000
   8.750   1.2879   0.01470   0.00862  -0.0771   0.0294   1.0000
   9.000   1.3123   0.01504   0.00899  -0.0766   0.0280   1.0000
   9.250   1.3361   0.01545   0.00940  -0.0760   0.0262   1.0000
   9.500   1.3577   0.01612   0.01009  -0.0751   0.0238   1.0000
   9.750   1.3807   0.01657   0.01060  -0.0744   0.0228   1.0000
  10.000   1.4044   0.01692   0.01100  -0.0739   0.0218   1.0000
  10.250   1.4274   0.01732   0.01142  -0.0732   0.0205   1.0000
  10.500   1.4492   0.01784   0.01194  -0.0724   0.0189   1.0000
  10.750   1.4685   0.01861   0.01276  -0.0712   0.0172   1.0000
  11.000   1.4910   0.01899   0.01318  -0.0705   0.0163   1.0000
  11.250   1.5123   0.01947   0.01369  -0.0697   0.0149   1.0000
  11.500   1.5286   0.02042   0.01466  -0.0682   0.0129   1.0000
  11.750   1.5491   0.02089   0.01519  -0.0672   0.0122   1.0000
  12.000   1.5675   0.02153   0.01587  -0.0660   0.0112   1.0000
  12.250   1.5829   0.02237   0.01674  -0.0643   0.0102   1.0000
  12.500   1.5922   0.02357   0.01803  -0.0618   0.0094   1.0000
  12.750   1.6043   0.02428   0.01883  -0.0596   0.0090   1.0000
  13.000   1.6137   0.02514   0.01978  -0.0571   0.0087   1.0000
  13.250   1.6222   0.02608   0.02079  -0.0547   0.0083   1.0000
  13.500   1.6294   0.02715   0.02195  -0.0523   0.0080   1.0000
  13.750   1.6352   0.02838   0.02326  -0.0500   0.0077   1.0000
  14.000   1.6378   0.02993   0.02490  -0.0476   0.0073   1.0000
  14.250   1.6362   0.03190   0.02699  -0.0452   0.0070   1.0000
  14.500   1.6277   0.03462   0.02986  -0.0428   0.0068   1.0000
  14.750   1.6283   0.03672   0.03208  -0.0414   0.0066   1.0000
  15.000   1.6303   0.03882   0.03429  -0.0403   0.0065   1.0000
  15.250   1.6301   0.04129   0.03688  -0.0395   0.0064   1.0000
  15.500   1.6285   0.04404   0.03975  -0.0391   0.0063   1.0000
  15.750   1.6242   0.04732   0.04316  -0.0390   0.0062   1.0000
  16.000   1.6187   0.05096   0.04693  -0.0394   0.0061   1.0000
  16.250   1.6098   0.05533   0.05145  -0.0404   0.0060   1.0000
  16.500   1.5998   0.06019   0.05645  -0.0419   0.0059   1.0000
  16.750   1.5864   0.06595   0.06236  -0.0443   0.0059   1.0000
  17.000   1.5708   0.07253   0.06910  -0.0474   0.0058   1.0000
  17.250   1.5518   0.08016   0.07689  -0.0514   0.0058   1.0000
  17.500   1.5301   0.08871   0.08561  -0.0561   0.0058   1.0000
  17.750   1.5056   0.09817   0.09523  -0.0614   0.0058   1.0000
  18.000   1.4779   0.10854   0.10577  -0.0674   0.0059   1.0000
  18.250   1.4493   0.11943   0.11681  -0.0738   0.0059   1.0000
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