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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 200,000
Max Cl/Cd: 90.9 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63110-il-200000.txt
Download as CSV file: xf-fx63110-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3491   0.08945   0.08613  -0.0371   1.0000   0.0614
  -8.000  -0.3653   0.08818   0.08494  -0.0341   1.0000   0.0628
  -7.750  -0.3864   0.08729   0.08415  -0.0305   1.0000   0.0632
  -7.500  -0.3793   0.06891   0.06564  -0.0718   0.9841   0.0678
  -7.250  -0.3615   0.07420   0.07110  -0.0515   0.9853   0.0697
  -7.000  -0.3374   0.07139   0.06827  -0.0542   0.9799   0.0723
  -6.750  -0.3049   0.05262   0.04893  -0.0937   0.9646   0.0813
  -6.500  -0.2640   0.03656   0.03177  -0.1088   0.9606   0.0553
  -6.250  -0.2279   0.03160   0.02626  -0.1141   0.9554   0.0552
  -6.000  -0.1884   0.02737   0.02149  -0.1187   0.9513   0.0549
  -5.750  -0.1453   0.02428   0.01782  -0.1230   0.9487   0.0569
  -5.500  -0.1045   0.02223   0.01564  -0.1265   0.9466   0.0595
  -5.250  -0.0711   0.02091   0.01415  -0.1279   0.9404   0.0615
  -5.000  -0.0317   0.01981   0.01283  -0.1302   0.9365   0.0651
  -4.750   0.0106   0.01879   0.01155  -0.1329   0.9340   0.0673
  -4.500   0.0523   0.01717   0.00997  -0.1360   0.9323   0.0718
  -4.250   0.0858   0.01650   0.00926  -0.1371   0.9258   0.0762
  -4.000   0.1253   0.01571   0.00838  -0.1391   0.9217   0.0805
  -3.750   0.1666   0.01473   0.00750  -0.1420   0.9187   0.0892
  -3.500   0.2046   0.01394   0.00674  -0.1440   0.9133   0.1002
  -3.250   0.2430   0.01314   0.00600  -0.1462   0.9065   0.1231
  -3.000   0.2891   0.01172   0.00516  -0.1506   0.9020   0.2427
  -2.750   0.3221   0.01124   0.00512  -0.1518   0.8924   0.4118
  -2.500   0.3580   0.01101   0.00502  -0.1531   0.8862   0.4694
  -2.250   0.3863   0.01104   0.00513  -0.1529   0.8764   0.5128
  -2.000   0.4191   0.01107   0.00515  -0.1534   0.8696   0.5495
  -1.750   0.4458   0.01119   0.00528  -0.1528   0.8595   0.5779
  -1.500   0.4761   0.01126   0.00532  -0.1528   0.8521   0.6038
  -1.250   0.5030   0.01134   0.00539  -0.1523   0.8424   0.6247
  -1.000   0.5312   0.01139   0.00544  -0.1519   0.8345   0.6444
  -0.750   0.5579   0.01145   0.00552  -0.1513   0.8253   0.6637
  -0.500   0.5852   0.01153   0.00558  -0.1507   0.8169   0.6827
  -0.250   0.6123   0.01159   0.00564  -0.1502   0.8082   0.7021
   0.000   0.6389   0.01166   0.00571  -0.1496   0.7994   0.7190
   0.250   0.6662   0.01168   0.00572  -0.1490   0.7910   0.7325
   0.500   0.6922   0.01173   0.00579  -0.1484   0.7815   0.7453
   0.750   0.7201   0.01175   0.00578  -0.1480   0.7735   0.7584
   1.000   0.7456   0.01180   0.00586  -0.1473   0.7633   0.7714
   1.250   0.7730   0.01183   0.00587  -0.1468   0.7547   0.7844
   1.500   0.7993   0.01186   0.00591  -0.1462   0.7445   0.7971
   1.750   0.8247   0.01188   0.00597  -0.1454   0.7343   0.8091
   2.000   0.8508   0.01186   0.00593  -0.1447   0.7235   0.8220
   2.250   0.8757   0.01181   0.00587  -0.1436   0.7100   0.8356
   2.500   0.8995   0.01177   0.00587  -0.1424   0.6957   0.8501
   2.750   0.9230   0.01175   0.00589  -0.1412   0.6827   0.8664
   3.000   0.9457   0.01174   0.00591  -0.1398   0.6705   0.8860
   3.250   0.9665   0.01169   0.00588  -0.1380   0.6585   0.9139
   3.500   0.9913   0.01160   0.00580  -0.1371   0.6458   1.0000
   3.750   1.0229   0.01176   0.00594  -0.1380   0.6307   1.0000
   4.000   1.0528   0.01194   0.00606  -0.1385   0.6146   1.0000
   4.250   1.0811   0.01212   0.00621  -0.1386   0.5963   1.0000
   4.500   1.1082   0.01230   0.00637  -0.1384   0.5766   1.0000
   4.750   1.1348   0.01252   0.00654  -0.1381   0.5570   1.0000
   5.000   1.1606   0.01277   0.00672  -0.1376   0.5364   1.0000
   5.250   1.1854   0.01304   0.00695  -0.1370   0.5127   1.0000
   5.500   1.2093   0.01338   0.00718  -0.1362   0.4876   1.0000
   5.750   1.2325   0.01377   0.00749  -0.1353   0.4604   1.0000
   6.000   1.2552   0.01422   0.00785  -0.1344   0.4328   1.0000
   6.250   1.2773   0.01472   0.00826  -0.1334   0.4056   1.0000
   6.500   1.2988   0.01526   0.00871  -0.1323   0.3774   1.0000
   6.750   1.3194   0.01584   0.00921  -0.1311   0.3442   1.0000
   7.000   1.3381   0.01655   0.00977  -0.1297   0.3050   1.0000
   7.250   1.3547   0.01743   0.01044  -0.1280   0.2631   1.0000
   7.500   1.3694   0.01849   0.01126  -0.1262   0.2240   1.0000
   7.750   1.3835   0.01962   0.01221  -0.1242   0.1862   1.0000
   8.000   1.3952   0.02093   0.01328  -0.1220   0.1486   1.0000
   8.250   1.4056   0.02231   0.01445  -0.1195   0.1187   1.0000
   8.500   1.4144   0.02369   0.01569  -0.1168   0.1011   1.0000
   8.750   1.4216   0.02503   0.01701  -0.1138   0.0907   1.0000
   9.000   1.4248   0.02669   0.01858  -0.1105   0.0839   1.0000
   9.250   1.4359   0.02784   0.01985  -0.1082   0.0787   1.0000
   9.500   1.4433   0.02931   0.02132  -0.1057   0.0744   1.0000
   9.750   1.4505   0.03105   0.02308  -0.1033   0.0708   1.0000
  10.000   1.4623   0.03234   0.02449  -0.1015   0.0676   1.0000
  10.250   1.4729   0.03377   0.02598  -0.0997   0.0646   1.0000
  10.500   1.4826   0.03559   0.02776  -0.0980   0.0617   1.0000
  10.750   1.4956   0.03730   0.02956  -0.0965   0.0594   1.0000
  11.000   1.5070   0.03876   0.03118  -0.0950   0.0569   1.0000
  11.250   1.5176   0.04033   0.03283  -0.0936   0.0546   1.0000
  11.500   1.5285   0.04205   0.03456  -0.0924   0.0524   1.0000
  11.750   1.5440   0.04426   0.03684  -0.0914   0.0500   1.0000
  12.000   1.5516   0.04605   0.03884  -0.0899   0.0483   1.0000
  12.250   1.5594   0.04800   0.04095  -0.0886   0.0464   1.0000
  12.500   1.5673   0.04999   0.04303  -0.0874   0.0447   1.0000
  12.750   1.5789   0.05212   0.04513  -0.0866   0.0428   1.0000
  13.000   1.5866   0.05504   0.04827  -0.0855   0.0412   1.0000
  13.250   1.5868   0.05771   0.05121  -0.0843   0.0400   1.0000
  13.500   1.5884   0.06056   0.05427  -0.0833   0.0387   1.0000
  13.750   1.5895   0.06351   0.05739  -0.0826   0.0376   1.0000
  14.000   1.5909   0.06640   0.06040  -0.0820   0.0365   1.0000
  14.250   1.5969   0.06926   0.06329  -0.0816   0.0353   1.0000
  14.500   1.5932   0.07408   0.06833  -0.0812   0.0343   1.0000
  14.750   1.5796   0.07854   0.07309  -0.0814   0.0338   1.0000
  15.000   1.5656   0.08355   0.07840  -0.0820   0.0333   1.0000
  15.250   1.5505   0.08902   0.08416  -0.0832   0.0329   1.0000
  15.500   1.5342   0.09497   0.09038  -0.0850   0.0324   1.0000
  15.750   1.5170   0.10146   0.09713  -0.0875   0.0321   1.0000
  16.000   1.4977   0.10861   0.10455  -0.0907   0.0320   1.0000
  16.250   1.4750   0.11687   0.11308  -0.0951   0.0320   1.0000
  16.500   1.4503   0.12606   0.12254  -0.1007   0.0320   1.0000
  16.750   1.4208   0.13697   0.13371  -0.1079   0.0322   1.0000
  17.000   1.3867   0.14999   0.14699  -0.1173   0.0327   1.0000
  17.250   1.3465   0.16605   0.16327  -0.1292   0.0336   1.0000
  17.500   1.2979   0.18754   0.18490  -0.1446   0.0348   1.0000
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