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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 200,000
Max Cl/Cd: 87.17 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63110-il-200000-n5.txt
Download as CSV file: xf-fx63110-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-110 AIRFOIL                               
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3581   0.09152   0.08791  -0.0438   1.0000   0.0213
  -9.250  -0.3655   0.08766   0.08410  -0.0442   1.0000   0.0213
  -9.000  -0.3771   0.08376   0.08029  -0.0443   1.0000   0.0216
  -8.750  -0.3807   0.07740   0.07398  -0.0494   0.9966   0.0220
  -8.500  -0.4204   0.04156   0.03768  -0.0975   0.9668   0.0224
  -8.250  -0.3973   0.02993   0.02476  -0.1134   0.9551   0.0243
  -8.000  -0.3672   0.02840   0.02313  -0.1159   0.9490   0.0252
  -7.750  -0.3351   0.02682   0.02135  -0.1185   0.9432   0.0263
  -7.500  -0.2994   0.02506   0.01929  -0.1218   0.9397   0.0281
  -7.250  -0.2675   0.02336   0.01720  -0.1239   0.9326   0.0301
  -7.000  -0.2315   0.02130   0.01482  -0.1269   0.9284   0.0317
  -6.750  -0.1938   0.02033   0.01377  -0.1296   0.9252   0.0335
  -6.500  -0.1610   0.01960   0.01292  -0.1311   0.9184   0.0356
  -6.250  -0.1243   0.01856   0.01167  -0.1333   0.9136   0.0376
  -5.750  -0.0532   0.01662   0.00937  -0.1370   0.9026   0.0416
  -5.500  -0.0170   0.01564   0.00833  -0.1390   0.8970   0.0438
  -5.250   0.0180   0.01505   0.00767  -0.1407   0.8907   0.0463
  -5.000   0.0515   0.01454   0.00708  -0.1419   0.8832   0.0491
  -4.750   0.0865   0.01400   0.00644  -0.1435   0.8770   0.0516
  -4.500   0.1177   0.01358   0.00593  -0.1442   0.8685   0.0537
  -4.250   0.1516   0.01309   0.00539  -0.1456   0.8617   0.0575
  -4.000   0.1817   0.01279   0.00508  -0.1462   0.8531   0.0629
  -3.750   0.2141   0.01249   0.00470  -0.1471   0.8459   0.0695
  -3.500   0.2439   0.01224   0.00443  -0.1476   0.8371   0.0796
  -3.250   0.2753   0.01201   0.00415  -0.1482   0.8287   0.0946
  -3.000   0.3047   0.01176   0.00391  -0.1486   0.8177   0.1144
  -2.750   0.3350   0.01144   0.00368  -0.1493   0.8078   0.1487
  -2.500   0.3668   0.01087   0.00354  -0.1506   0.7990   0.2810
  -2.250   0.3964   0.01069   0.00353  -0.1510   0.7906   0.3607
  -2.000   0.4260   0.01056   0.00350  -0.1513   0.7828   0.4120
  -1.750   0.4547   0.01047   0.00353  -0.1514   0.7744   0.4545
  -1.500   0.4835   0.01044   0.00357  -0.1514   0.7667   0.4923
  -1.250   0.5117   0.01046   0.00363  -0.1513   0.7582   0.5235
  -1.000   0.5402   0.01051   0.00365  -0.1512   0.7506   0.5486
  -0.750   0.5683   0.01056   0.00370  -0.1511   0.7420   0.5715
  -0.500   0.5966   0.01062   0.00373  -0.1509   0.7344   0.5916
  -0.250   0.6243   0.01067   0.00380  -0.1507   0.7256   0.6112
   0.000   0.6523   0.01074   0.00383  -0.1505   0.7178   0.6277
   0.250   0.6798   0.01079   0.00390  -0.1502   0.7088   0.6397
   0.500   0.7076   0.01086   0.00394  -0.1500   0.7005   0.6515
   0.750   0.7352   0.01093   0.00401  -0.1498   0.6912   0.6633
   1.000   0.7626   0.01100   0.00409  -0.1495   0.6825   0.6738
   1.250   0.7901   0.01109   0.00417  -0.1493   0.6731   0.6840
   1.500   0.8174   0.01117   0.00426  -0.1490   0.6632   0.6945
   1.750   0.8445   0.01127   0.00436  -0.1487   0.6536   0.7046
   2.000   0.8713   0.01137   0.00445  -0.1483   0.6411   0.7153
   2.250   0.8975   0.01148   0.00454  -0.1477   0.6252   0.7259
   2.500   0.9233   0.01160   0.00464  -0.1471   0.6081   0.7360
   2.750   0.9494   0.01173   0.00476  -0.1466   0.5928   0.7470
   3.000   0.9755   0.01186   0.00491  -0.1461   0.5784   0.7589
   3.250   1.0012   0.01200   0.00508  -0.1456   0.5641   0.7709
   3.500   1.0266   0.01215   0.00525  -0.1449   0.5488   0.7842
   3.750   1.0509   0.01232   0.00541  -0.1441   0.5304   0.8006
   4.250   1.0960   0.01267   0.00579  -0.1416   0.4909   0.8461
   4.500   1.1140   0.01281   0.00594  -0.1394   0.4706   0.8884
   4.750   1.1341   0.01301   0.00610  -0.1377   0.4482   1.0000
   5.000   1.1585   0.01345   0.00643  -0.1372   0.4234   1.0000
   5.250   1.1824   0.01391   0.00678  -0.1366   0.3972   1.0000
   5.500   1.2057   0.01440   0.00716  -0.1360   0.3700   1.0000
   5.750   1.2281   0.01495   0.00758  -0.1352   0.3379   1.0000
   6.000   1.2495   0.01557   0.00804  -0.1342   0.3028   1.0000
   6.250   1.2699   0.01627   0.00857  -0.1332   0.2685   1.0000
   6.750   1.3095   0.01777   0.00981  -0.1310   0.2110   1.0000
   7.000   1.3289   0.01854   0.01047  -0.1298   0.1878   1.0000
   7.250   1.3478   0.01933   0.01116  -0.1286   0.1648   1.0000
   7.500   1.3662   0.02013   0.01188  -0.1273   0.1424   1.0000
   8.000   1.3998   0.02191   0.01349  -0.1243   0.1033   1.0000
   8.250   1.4153   0.02283   0.01437  -0.1226   0.0913   1.0000
   8.500   1.4287   0.02378   0.01530  -0.1206   0.0826   1.0000
   8.750   1.4423   0.02464   0.01622  -0.1186   0.0761   1.0000
   9.000   1.4527   0.02572   0.01729  -0.1162   0.0703   1.0000
   9.250   1.4653   0.02665   0.01833  -0.1141   0.0658   1.0000
   9.500   1.4762   0.02771   0.01946  -0.1120   0.0618   1.0000
   9.750   1.4841   0.02902   0.02080  -0.1097   0.0587   1.0000
  10.000   1.4939   0.03023   0.02211  -0.1076   0.0564   1.0000
  10.250   1.5037   0.03149   0.02348  -0.1057   0.0541   1.0000
  10.500   1.5126   0.03286   0.02494  -0.1039   0.0518   1.0000
  10.750   1.5196   0.03444   0.02659  -0.1021   0.0498   1.0000
  11.000   1.5235   0.03636   0.02855  -0.1003   0.0480   1.0000
  11.250   1.5326   0.03791   0.03024  -0.0989   0.0464   1.0000
  11.500   1.5406   0.03959   0.03204  -0.0976   0.0446   1.0000
  11.750   1.5479   0.04138   0.03394  -0.0964   0.0429   1.0000
  12.000   1.5534   0.04341   0.03604  -0.0953   0.0413   1.0000
  12.250   1.5557   0.04582   0.03852  -0.0942   0.0399   1.0000
  12.500   1.5599   0.04815   0.04096  -0.0932   0.0386   1.0000
  12.750   1.5655   0.05039   0.04335  -0.0925   0.0373   1.0000
  13.000   1.5698   0.05281   0.04593  -0.0918   0.0359   1.0000
  13.250   1.5729   0.05543   0.04867  -0.0914   0.0346   1.0000
  13.500   1.5742   0.05834   0.05167  -0.0910   0.0335   1.0000
  13.750   1.5724   0.06171   0.05511  -0.0908   0.0324   1.0000
  14.000   1.5735   0.06485   0.05841  -0.0907   0.0314   1.0000
  14.250   1.5751   0.06801   0.06175  -0.0908   0.0303   1.0000
  14.500   1.5754   0.07143   0.06532  -0.0911   0.0291   1.0000
  14.750   1.5746   0.07511   0.06914  -0.0916   0.0281   1.0000
  15.000   1.5722   0.07911   0.07325  -0.0924   0.0272   1.0000
  15.250   1.5677   0.08352   0.07775  -0.0935   0.0263   1.0000
  15.500   1.5648   0.08785   0.08224  -0.0945   0.0255   1.0000
  15.750   1.5624   0.09223   0.08684  -0.0958   0.0245   1.0000
  16.000   1.5586   0.09692   0.09171  -0.0973   0.0236   1.0000
  16.250   1.5541   0.10185   0.09683  -0.0992   0.0228   1.0000
  16.500   1.5489   0.10699   0.10211  -0.1013   0.0221   1.0000
  16.750   1.5432   0.11235   0.10759  -0.1038   0.0215   1.0000
  17.000   1.5362   0.11795   0.11329  -0.1065   0.0210   1.0000
  17.250   1.5296   0.12367   0.11921  -0.1092   0.0204   1.0000
  17.500   1.5225   0.12960   0.12535  -0.1123   0.0197   1.0000
  17.750   1.5147   0.13581   0.13174  -0.1158   0.0190   1.0000
  18.000   1.5069   0.14207   0.13817  -0.1195   0.0185   1.0000
  18.250   1.4988   0.14857   0.14481  -0.1235   0.0180   1.0000
  18.500   1.4906   0.15517   0.15154  -0.1278   0.0176   1.0000
  18.750   1.4823   0.16193   0.15842  -0.1323   0.0173   1.0000
  19.000   1.4738   0.16884   0.16546  -0.1370   0.0170   1.0000
  19.250   1.4660   0.17563   0.17234  -0.1417   0.0167   1.0000
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