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FX 63-145 AIRFOIL (fx63145-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 63-145 AIRFOIL (fx63145-il)
Reynolds number: 1,000,000
Max Cl/Cd: 81.35 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63145-il-1000000-n5.txt
Download as CSV file: xf-fx63145-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-145 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1612   0.10171   0.09660  -0.0839   0.1147   0.0047
 -11.250  -0.1675   0.09599   0.09091  -0.0862   0.1169   0.0050
 -11.000  -0.1620   0.09341   0.08834  -0.0874   0.1144   0.0052
 -10.750  -0.1614   0.08911   0.08405  -0.0892   0.1150   0.0051
 -10.500  -0.1557   0.08660   0.08155  -0.0905   0.1142   0.0054
 -10.250  -0.1551   0.08256   0.07754  -0.0923   0.1136   0.0055
 -10.000  -0.1551   0.07848   0.07347  -0.0943   0.1128   0.0056
  -9.750  -0.1586   0.07346   0.06849  -0.0968   0.1126   0.0056
  -9.500  -0.1635   0.06798   0.06305  -0.0998   0.1137   0.0059
  -9.250  -0.2118   0.05168   0.04673  -0.1114   0.1169   0.0054
  -9.000  -0.2261   0.04754   0.04254  -0.1141   0.1167   0.0054
  -8.750  -0.2602   0.04238   0.03729  -0.1145   0.1168   0.0053
  -8.500  -0.2684   0.03933   0.03411  -0.1158   0.1171   0.0053
  -8.250  -0.2627   0.03747   0.03213  -0.1161   0.1165   0.0055
  -8.000  -0.2561   0.03480   0.02926  -0.1163   0.1151   0.0056
  -7.750  -0.2458   0.03193   0.02617  -0.1165   0.1142   0.0057
  -7.500  -0.2309   0.02936   0.02336  -0.1166   0.1131   0.0058
  -4.000   0.1299   0.01376   0.00555  -0.1181   0.0843   0.0047
  -3.750   0.1593   0.01333   0.00506  -0.1186   0.0832   0.0047
  -3.500   0.1889   0.01300   0.00467  -0.1192   0.0823   0.0046
  -3.250   0.2186   0.01272   0.00433  -0.1197   0.0820   0.0046
  -3.000   0.2484   0.01250   0.00405  -0.1201   0.0818   0.0047
  -2.750   0.2780   0.01232   0.00383  -0.1206   0.0816   0.0047
  -2.500   0.3074   0.01219   0.00365  -0.1209   0.0814   0.0047
  -2.250   0.3368   0.01209   0.00351  -0.1213   0.0812   0.0048
  -2.000   0.3663   0.01198   0.00334  -0.1216   0.0810   0.0049
  -1.750   0.3956   0.01192   0.00322  -0.1219   0.0808   0.0053
  -1.500   0.4246   0.01190   0.00315  -0.1221   0.0806   0.0059
  -1.250   0.4534   0.01191   0.00312  -0.1223   0.0804   0.0067
  -1.000   0.4820   0.01194   0.00313  -0.1225   0.0801   0.0074
  -0.750   0.5106   0.01196   0.00315  -0.1226   0.0799   0.0165
  -0.500   0.5391   0.01200   0.00319  -0.1228   0.0796   0.0297
  -0.250   0.5674   0.01206   0.00325  -0.1229   0.0794   0.0334
   0.000   0.5956   0.01213   0.00330  -0.1230   0.0791   0.0354
   0.250   0.6237   0.01221   0.00337  -0.1230   0.0789   0.0370
   0.500   0.6517   0.01230   0.00344  -0.1231   0.0786   0.0382
   0.750   0.6798   0.01237   0.00351  -0.1232   0.0783   0.0430
   1.000   0.7080   0.01243   0.00360  -0.1233   0.0781   0.0617
   1.250   0.7359   0.01253   0.00370  -0.1234   0.0778   0.0645
   1.500   0.7636   0.01264   0.00380  -0.1234   0.0775   0.0664
   1.750   0.7914   0.01274   0.00389  -0.1234   0.0769   0.0684
   2.000   0.8189   0.01285   0.00400  -0.1234   0.0765   0.0703
   2.250   0.8465   0.01297   0.00412  -0.1234   0.0761   0.0756
   2.500   0.8740   0.01308   0.00426  -0.1235   0.0757   0.0912
   2.750   0.9012   0.01322   0.00440  -0.1234   0.0752   0.0947
   3.000   0.9281   0.01337   0.00456  -0.1233   0.0747   0.0965
   3.250   0.9554   0.01349   0.00468  -0.1233   0.0744   0.0979
   3.500   0.9828   0.01359   0.00480  -0.1233   0.0742   0.1010
   3.750   1.0100   0.01370   0.00492  -0.1233   0.0739   0.1036
   4.000   1.0371   0.01382   0.00506  -0.1233   0.0734   0.1059
   4.500   1.0908   0.01409   0.00536  -0.1231   0.0713   0.1139
   4.750   1.1174   0.01424   0.00555  -0.1231   0.0607   0.1367
   5.000   1.1431   0.01446   0.00575  -0.1228   0.0596   0.1424
   5.250   1.1689   0.01467   0.00592  -0.1226   0.0560   0.1459
   5.500   1.1942   0.01490   0.00619  -0.1223   0.0535   0.1490
   5.750   1.2195   0.01514   0.00646  -0.1220   0.0525   0.1548
   6.000   1.2444   0.01540   0.00679  -0.1217   0.0509   0.1720
   6.250   1.2684   0.01571   0.00715  -0.1212   0.0488   0.1902
   6.500   1.2923   0.01603   0.00749  -0.1207   0.0462   0.1963
   6.750   1.3172   0.01624   0.00773  -0.1203   0.0449   0.1999
   7.000   1.3415   0.01649   0.00802  -0.1199   0.0423   0.2079
   7.250   1.3564   0.01742   0.00880  -0.1181   0.0101   0.2383
   7.500   1.3758   0.01798   0.00937  -0.1169   0.0025   0.2494
   7.750   1.3969   0.01838   0.00981  -0.1160   0.0020   0.2549
   8.000   1.4178   0.01877   0.01027  -0.1150   0.0018   0.2639
   8.250   1.4383   0.01917   0.01077  -0.1141   0.0017   0.3053
   8.500   1.4570   0.01963   0.01130  -0.1128   0.0016   0.3179
   8.750   1.4733   0.02007   0.01185  -0.1112   0.0015   0.3580
   9.000   1.4878   0.02057   0.01244  -0.1092   0.0014   0.3802
   9.250   1.5025   0.02110   0.01312  -0.1074   0.0014   0.4320
   9.500   1.5153   0.02172   0.01386  -0.1054   0.0013   0.4561
   9.750   1.5279   0.02238   0.01468  -0.1035   0.0013   0.5109
  10.000   1.5389   0.02314   0.01560  -0.1014   0.0013   0.5524
  10.250   1.5472   0.02408   0.01663  -0.0991   0.0012   0.5667
  10.500   1.5535   0.02520   0.01786  -0.0967   0.0012   0.5769
  10.750   1.5576   0.02656   0.01935  -0.0945   0.0011   0.5926
  11.000   1.5609   0.02809   0.02101  -0.0924   0.0011   0.6146
  11.250   1.5669   0.02957   0.02259  -0.0909   0.0010   0.6304
  11.500   1.5713   0.03131   0.02445  -0.0896   0.0010   0.6443
  11.750   1.5748   0.03328   0.02654  -0.0886   0.0010   0.6614
  12.000   1.5779   0.03544   0.02882  -0.0878   0.0010   0.6805
  12.250   1.5802   0.03780   0.03129  -0.0872   0.0010   0.6910
  12.500   1.5819   0.04035   0.03395  -0.0867   0.0010   0.6992
  12.750   1.5825   0.04314   0.03685  -0.0865   0.0009   0.7072
  13.250   1.5821   0.04917   0.04313  -0.0864   0.0009   0.7350
  13.500   1.5801   0.05253   0.04661  -0.0866   0.0009   0.7504
  13.750   1.5783   0.05597   0.05020  -0.0870   0.0009   0.7697
  14.000   1.5755   0.05964   0.05405  -0.0875   0.0009   0.8074
  14.250   1.5684   0.06290   0.05767  -0.0870   0.0008   1.0000
  14.500   1.5643   0.06693   0.06180  -0.0877   0.0008   1.0000
  14.750   1.5601   0.07112   0.06609  -0.0887   0.0008   1.0000
  15.000   1.5558   0.07546   0.07052  -0.0897   0.0008   1.0000
  15.250   1.5501   0.08010   0.07527  -0.0910   0.0008   1.0000
  15.500   1.5442   0.08492   0.08019  -0.0924   0.0007   1.0000
  15.750   1.5387   0.08978   0.08515  -0.0940   0.0007   1.0000
  16.000   1.5322   0.09494   0.09041  -0.0958   0.0007   1.0000
  16.250   1.5254   0.10024   0.09583  -0.0977   0.0007   1.0000
  16.500   1.5182   0.10570   0.10139  -0.0998   0.0007   1.0000
  16.750   1.5114   0.11119   0.10698  -0.1020   0.0007   1.0000
  17.000   1.5032   0.11701   0.11291  -0.1045   0.0006   1.0000
  17.250   1.4951   0.12292   0.11893  -0.1072   0.0006   1.0000
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