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FX 63-110 AIRFOIL (fx63110-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: FX 63-110 AIRFOIL (fx63110-il)
Reynolds number: 100,000
Max Cl/Cd: 64.93 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx63110-il-100000.txt
Download as CSV file: xf-fx63110-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3261   0.10631   0.10125  -0.0387   1.0000   0.1069
  -9.000  -0.3500   0.10557   0.10067  -0.0415   1.0000   0.1090
  -8.750  -0.3788   0.10491   0.10021  -0.0424   1.0000   0.1095
  -8.500  -0.3336   0.09791   0.09309  -0.0381   1.0000   0.1131
  -8.250  -0.3296   0.09564   0.09087  -0.0363   1.0000   0.1164
  -8.000  -0.3379   0.09389   0.08922  -0.0350   1.0000   0.1206
  -7.750  -0.3609   0.09301   0.08848  -0.0330   1.0000   0.1231
  -7.500  -0.3932   0.09290   0.08854  -0.0297   1.0000   0.1240
  -7.250  -0.4283   0.09219   0.08799  -0.0301   1.0000   0.1249
  -7.000  -0.4494   0.08842   0.08434  -0.0349   1.0000   0.1259
  -6.750  -0.4211   0.08723   0.08310  -0.0215   1.0000   0.1304
  -6.500  -0.4281   0.08567   0.08161  -0.0197   1.0000   0.1344
  -6.000  -0.4516   0.07849   0.07457  -0.0281   1.0000   0.1435
  -5.750  -0.4269   0.07642   0.07247  -0.0271   0.9957   0.1515
  -5.500  -0.3984   0.07091   0.06692  -0.0366   0.9886   0.1633
  -5.250  -0.3674   0.06613   0.06207  -0.0449   0.9822   0.1793
  -5.000  -0.2499   0.03742   0.03058  -0.0936   0.9817   0.0948
  -4.750  -0.2052   0.03380   0.02642  -0.0986   0.9776   0.0950
  -4.500  -0.1598   0.03068   0.02291  -0.1033   0.9742   0.0965
  -4.250  -0.1182   0.02874   0.02072  -0.1067   0.9697   0.0991
  -4.000  -0.0779   0.02743   0.01914  -0.1096   0.9640   0.1044
  -3.750  -0.0318   0.02617   0.01748  -0.1130   0.9600   0.1082
  -3.500   0.0029   0.02488   0.01620  -0.1148   0.9534   0.1151
  -3.250   0.0452   0.02403   0.01521  -0.1175   0.9481   0.1240
  -3.000   0.0829   0.02304   0.01437  -0.1196   0.9421   0.1365
  -2.750   0.1237   0.02210   0.01358  -0.1222   0.9357   0.1596
  -2.500   0.1780   0.02030   0.01287  -0.1282   0.9324   0.3322
  -2.250   0.2094   0.02024   0.01344  -0.1285   0.9233   0.5198
  -2.000   0.2504   0.02058   0.01377  -0.1300   0.9175   0.5851
  -1.750   0.2759   0.02091   0.01410  -0.1291   0.9074   0.6194
  -1.500   0.3166   0.02097   0.01414  -0.1305   0.9022   0.6556
  -1.250   0.3372   0.02125   0.01448  -0.1285   0.8920   0.6817
  -1.000   0.3766   0.02111   0.01435  -0.1296   0.8870   0.7108
  -0.750   0.4000   0.02127   0.01451  -0.1284   0.8772   0.7368
  -0.500   0.4376   0.02099   0.01423  -0.1291   0.8720   0.7642
  -0.250   0.4613   0.02099   0.01425  -0.1279   0.8628   0.7873
   0.000   0.4965   0.02066   0.01390  -0.1285   0.8564   0.8106
   0.250   0.5214   0.02057   0.01381  -0.1275   0.8474   0.8321
   0.500   0.5515   0.02024   0.01348  -0.1271   0.8402   0.8553
   0.750   0.5719   0.02016   0.01343  -0.1252   0.8304   0.8788
   1.000   0.6006   0.01974   0.01301  -0.1244   0.8233   0.9056
   1.250   0.6179   0.01961   0.01294  -0.1221   0.8124   0.9407
   1.500   0.6676   0.01909   0.01240  -0.1257   0.8062   1.0000
   1.750   0.7049   0.01930   0.01258  -0.1282   0.7949   1.0000
   2.000   0.7543   0.01895   0.01216  -0.1317   0.7889   1.0000
   2.250   0.7878   0.01918   0.01240  -0.1332   0.7763   1.0000
   2.500   0.8232   0.01929   0.01249  -0.1347   0.7648   1.0000
   2.750   0.8655   0.01900   0.01215  -0.1367   0.7566   1.0000
   3.000   0.8980   0.01896   0.01209  -0.1372   0.7425   1.0000
   3.250   0.9299   0.01887   0.01198  -0.1375   0.7279   1.0000
   3.500   0.9610   0.01884   0.01194  -0.1376   0.7135   1.0000
   3.750   0.9913   0.01887   0.01197  -0.1376   0.6996   1.0000
   4.000   1.0214   0.01892   0.01201  -0.1376   0.6858   1.0000
   4.250   1.0513   0.01897   0.01205  -0.1375   0.6720   1.0000
   4.500   1.0808   0.01902   0.01212  -0.1373   0.6578   1.0000
   4.750   1.1097   0.01910   0.01220  -0.1370   0.6429   1.0000
   5.000   1.1369   0.01918   0.01229  -0.1364   0.6260   1.0000
   5.250   1.1631   0.01921   0.01235  -0.1355   0.6067   1.0000
   5.500   1.1895   0.01914   0.01223  -0.1345   0.5855   1.0000
   5.750   1.2143   0.01919   0.01227  -0.1334   0.5632   1.0000
   6.000   1.2381   0.01935   0.01246  -0.1323   0.5405   1.0000
   6.250   1.2620   0.01954   0.01262  -0.1311   0.5171   1.0000
   6.500   1.2837   0.01977   0.01279  -0.1296   0.4891   1.0000
   6.750   1.3033   0.02013   0.01308  -0.1278   0.4574   1.0000
   7.000   1.3210   0.02064   0.01352  -0.1258   0.4225   1.0000
   7.250   1.3375   0.02129   0.01409  -0.1238   0.3862   1.0000
   7.500   1.3521   0.02207   0.01474  -0.1215   0.3479   1.0000
   7.750   1.3637   0.02304   0.01556  -0.1190   0.3039   1.0000
   8.000   1.3716   0.02438   0.01662  -0.1160   0.2582   1.0000
   8.250   1.3762   0.02613   0.01804  -0.1128   0.2154   1.0000
   8.500   1.3795   0.02809   0.01968  -0.1095   0.1820   1.0000
   8.750   1.3846   0.02988   0.02131  -0.1064   0.1571   1.0000
   9.000   1.3912   0.03164   0.02292  -0.1037   0.1400   1.0000
   9.250   1.4020   0.03340   0.02462  -0.1015   0.1271   1.0000
   9.500   1.4163   0.03520   0.02638  -0.0998   0.1170   1.0000
   9.750   1.4350   0.03711   0.02814  -0.0989   0.1087   1.0000
  10.000   1.4536   0.03880   0.02998  -0.0977   0.1020   1.0000
  10.250   1.4841   0.04112   0.03219  -0.0984   0.0956   1.0000
  10.500   1.5002   0.04295   0.03428  -0.0970   0.0908   1.0000
  10.750   1.5288   0.04523   0.03649  -0.0976   0.0857   1.0000
  11.000   1.5498   0.04805   0.03956  -0.0971   0.0818   1.0000
  11.250   1.5606   0.05036   0.04218  -0.0952   0.0786   1.0000
  11.500   1.5725   0.05270   0.04471  -0.0936   0.0755   1.0000
  11.750   1.5995   0.05693   0.04895  -0.0948   0.0716   1.0000
  12.000   1.5906   0.05935   0.05180  -0.0907   0.0705   1.0000
  12.250   1.5812   0.06231   0.05515  -0.0871   0.0694   1.0000
  12.500   1.5699   0.06561   0.05882  -0.0840   0.0682   1.0000
  12.750   1.5571   0.06918   0.06272  -0.0815   0.0671   1.0000
  13.000   1.5439   0.07302   0.06685  -0.0796   0.0660   1.0000
  13.250   1.5300   0.07719   0.07129  -0.0783   0.0651   1.0000
  13.500   1.5203   0.08129   0.07559  -0.0775   0.0639   1.0000
  13.750   1.4999   0.08658   0.08117  -0.0774   0.0637   1.0000
  14.000   1.4635   0.09375   0.08872  -0.0786   0.0643   1.0000
  14.250   1.4159   0.10339   0.09877  -0.0822   0.0658   1.0000
  14.500   1.3708   0.11423   0.10993  -0.0879   0.0675   1.0000
  14.750   1.3296   0.12605   0.12198  -0.0952   0.0693   1.0000
  15.000   1.2945   0.13851   0.13455  -0.1033   0.0707   1.0000
  15.250   1.2685   0.15060   0.14671  -0.1109   0.0717   1.0000
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