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S1210 12% (s1210-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: S1210 12% (s1210-il)
Reynolds number: 1,000,000
Max Cl/Cd: 147.98 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1210-il-1000000.txt
Download as CSV file: xf-s1210-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1210 12%                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0031   0.09748   0.09585  -0.0804   0.9737   0.0108
 -10.000   0.0085   0.09406   0.09244  -0.0826   0.9723   0.0110
  -9.750  -0.1001   0.10687   0.10516  -0.0720   0.9814   0.0106
  -9.500  -0.0828   0.10406   0.10235  -0.0748   0.9805   0.0108
  -9.250  -0.0654   0.10097   0.09926  -0.0781   0.9797   0.0111
  -7.750  -0.0035   0.07619   0.07452  -0.0969   0.9604   0.0137
  -7.500   0.0032   0.07379   0.07213  -0.0974   0.9529   0.0138
  -7.250   0.0191   0.07135   0.06970  -0.0998   0.9482   0.0141
  -7.000   0.0262   0.06954   0.06789  -0.0997   0.9373   0.0145
  -6.750   0.0385   0.06619   0.06454  -0.1027   0.9274   0.0150
  -6.500   0.0572   0.06118   0.05950  -0.1093   0.9165   0.0157
  -6.250   0.1532   0.02371   0.02125  -0.1898   0.8933   0.0179
  -5.750   0.3406   0.01317   0.00919  -0.2289   0.8528   0.0158
  -5.500   0.3910   0.01202   0.00765  -0.2344   0.8154   0.0157
  -5.250   0.4287   0.01121   0.00652  -0.2368   0.7786   0.0154
  -5.000   0.4619   0.01068   0.00573  -0.2382   0.7458   0.0154
  -4.750   0.4948   0.01032   0.00517  -0.2394   0.7166   0.0156
  -4.500   0.5276   0.01007   0.00474  -0.2405   0.6914   0.0160
  -4.250   0.5605   0.00987   0.00438  -0.2417   0.6689   0.0164
  -4.000   0.5930   0.00973   0.00409  -0.2427   0.6490   0.0167
  -3.750   0.6274   0.00952   0.00373  -0.2442   0.6310   0.0170
  -3.500   0.6630   0.00929   0.00334  -0.2459   0.6146   0.0176
  -3.250   0.6958   0.00918   0.00312  -0.2470   0.6000   0.0185
  -3.000   0.7274   0.00912   0.00297  -0.2477   0.5873   0.0197
  -2.750   0.7585   0.00909   0.00284  -0.2483   0.5759   0.0207
  -2.500   0.7900   0.00905   0.00272  -0.2490   0.5651   0.0236
  -2.250   0.8274   0.00875   0.00256  -0.2512   0.5554   0.0941
  -2.000   0.8640   0.00851   0.00257  -0.2534   0.5457   0.2220
  -1.750   0.8931   0.00856   0.00262  -0.2534   0.5374   0.2395
  -1.500   0.9209   0.00870   0.00270  -0.2533   0.5290   0.2540
  -1.250   0.9495   0.00877   0.00277  -0.2533   0.5219   0.2655
  -1.000   0.9776   0.00889   0.00282  -0.2531   0.5149   0.2714
  -0.750   1.0066   0.00895   0.00288  -0.2532   0.5089   0.2777
  -0.500   1.0348   0.00904   0.00294  -0.2531   0.5028   0.2829
  -0.250   1.0627   0.00917   0.00300  -0.2530   0.4965   0.2874
   0.000   1.0921   0.00921   0.00305  -0.2532   0.4918   0.2920
   0.250   1.1206   0.00929   0.00312  -0.2532   0.4867   0.2965
   0.500   1.1484   0.00943   0.00320  -0.2530   0.4815   0.3006
   0.750   1.1771   0.00949   0.00327  -0.2531   0.4770   0.3052
   1.000   1.2057   0.00956   0.00335  -0.2531   0.4715   0.3112
   1.250   1.2333   0.00971   0.00345  -0.2529   0.4652   0.3170
   1.500   1.2618   0.00978   0.00354  -0.2530   0.4606   0.3240
   1.750   1.2902   0.00986   0.00363  -0.2529   0.4563   0.3322
   2.000   1.3181   0.00997   0.00375  -0.2529   0.4521   0.3411
   2.250   1.3456   0.01013   0.00389  -0.2527   0.4474   0.3515
   2.500   1.3742   0.01017   0.00399  -0.2528   0.4431   0.3639
   2.750   1.4021   0.01028   0.00412  -0.2527   0.4378   0.3780
   3.000   1.4295   0.01044   0.00427  -0.2525   0.4326   0.3934
   3.250   1.4576   0.01051   0.00440  -0.2525   0.4279   0.4103
   3.500   1.4854   0.01062   0.00453  -0.2524   0.4221   0.4289
   3.750   1.5125   0.01079   0.00471  -0.2522   0.4166   0.4490
   4.000   1.5404   0.01088   0.00486  -0.2522   0.4124   0.4709
   4.250   1.5683   0.01098   0.00503  -0.2521   0.4082   0.4955
   4.500   1.5955   0.01112   0.00521  -0.2520   0.4029   0.5219
   4.750   1.6228   0.01127   0.00541  -0.2518   0.3974   0.5514
   5.000   1.6507   0.01137   0.00559  -0.2518   0.3918   0.5866
   5.250   1.6779   0.01154   0.00582  -0.2517   0.3854   0.6261
   5.500   1.7055   0.01166   0.00604  -0.2516   0.3794   0.6705
   5.750   1.7328   0.01182   0.00627  -0.2515   0.3712   0.7229
   6.000   1.7598   0.01197   0.00653  -0.2513   0.3624   0.7909
   6.250   1.7787   0.01202   0.00675  -0.2494   0.3513   0.9432
   6.500   1.8020   0.01230   0.00698  -0.2484   0.3360   1.0000
   6.750   1.8254   0.01273   0.00730  -0.2476   0.3149   1.0000
   7.000   1.8470   0.01333   0.00776  -0.2465   0.2899   1.0000
   7.250   1.8677   0.01399   0.00827  -0.2452   0.2643   1.0000
   7.500   1.8878   0.01469   0.00883  -0.2438   0.2411   1.0000
   7.750   1.9078   0.01535   0.00939  -0.2424   0.2218   1.0000
   8.000   1.9277   0.01598   0.00994  -0.2409   0.2061   1.0000
   8.250   1.9465   0.01665   0.01052  -0.2392   0.1905   1.0000
   8.500   1.9634   0.01736   0.01115  -0.2372   0.1750   1.0000
   8.750   1.9790   0.01809   0.01181  -0.2349   0.1605   1.0000
   9.000   1.9945   0.01878   0.01246  -0.2326   0.1493   1.0000
   9.250   2.0095   0.01949   0.01314  -0.2303   0.1398   1.0000
   9.500   2.0239   0.02027   0.01387  -0.2279   0.1303   1.0000
   9.750   2.0389   0.02100   0.01459  -0.2256   0.1222   1.0000
  10.000   2.0513   0.02188   0.01545  -0.2230   0.1142   1.0000
  10.250   2.0664   0.02259   0.01618  -0.2208   0.1095   1.0000
  10.500   2.0784   0.02352   0.01710  -0.2181   0.1039   1.0000
  10.750   2.0920   0.02433   0.01795  -0.2158   0.1000   1.0000
  11.000   2.1044   0.02523   0.01886  -0.2133   0.0957   1.0000
  11.250   2.1146   0.02630   0.01995  -0.2106   0.0915   1.0000
  11.500   2.1254   0.02734   0.02102  -0.2081   0.0872   1.0000
  11.750   2.1354   0.02845   0.02215  -0.2055   0.0834   1.0000
  12.000   2.1427   0.02980   0.02352  -0.2027   0.0794   1.0000
  12.250   2.1513   0.03108   0.02485  -0.2001   0.0765   1.0000
  12.500   2.1609   0.03230   0.02614  -0.1978   0.0747   1.0000
  12.750   2.1678   0.03379   0.02768  -0.1953   0.0718   1.0000
  13.000   2.1712   0.03565   0.02956  -0.1926   0.0681   1.0000
  13.250   2.1763   0.03743   0.03140  -0.1902   0.0653   1.0000
  13.500   2.1814   0.03926   0.03330  -0.1881   0.0627   1.0000
  13.750   2.1796   0.04189   0.03593  -0.1855   0.0575   1.0000
  14.000   2.1800   0.04444   0.03854  -0.1835   0.0529   1.0000
  14.250   2.1763   0.04758   0.04170  -0.1815   0.0482   1.0000
  14.500   2.1696   0.05129   0.04544  -0.1797   0.0418   1.0000
  14.750   2.1488   0.05702   0.05116  -0.1779   0.0322   1.0000
  15.000   2.1272   0.06333   0.05750  -0.1768   0.0240   1.0000
  15.250   2.1196   0.06791   0.06216  -0.1763   0.0219   1.0000
  15.500   2.0948   0.07527   0.06957  -0.1762   0.0153   1.0000
  15.750   2.0793   0.08142   0.07582  -0.1764   0.0122   1.0000
  16.000   2.0589   0.08853   0.08302  -0.1770   0.0082   1.0000
  16.250   2.0418   0.09523   0.08981  -0.1778   0.0056   1.0000
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