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FX 63-100 AIRFOIL (fx63100-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 63-100 AIRFOIL (fx63100-il)
Reynolds number: 500,000
Max Cl/Cd: 106.21 at α=2°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx63100-il-500000-n5.txt
Download as CSV file: xf-fx63100-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 63-100 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2756   0.10397   0.10177  -0.0372   1.0000   0.0087
 -10.750  -0.2715   0.09892   0.09673  -0.0398   0.9991   0.0088
 -10.250  -0.6007   0.03371   0.03083  -0.1003   0.9871   0.0079
 -10.000  -0.5732   0.02662   0.02314  -0.1128   0.9808   0.0082
  -9.750  -0.5401   0.02390   0.02014  -0.1178   0.9780   0.0084
  -9.500  -0.5104   0.02217   0.01821  -0.1205   0.9736   0.0087
  -9.250  -0.4790   0.02058   0.01640  -0.1231   0.9694   0.0090
  -8.750  -0.4172   0.01790   0.01332  -0.1270   0.9596   0.0098
  -8.250  -0.3542   0.01588   0.01092  -0.1300   0.9488   0.0108
  -8.000  -0.3197   0.01484   0.00975  -0.1322   0.9442   0.0116
  -7.750  -0.2844   0.01418   0.00900  -0.1342   0.9398   0.0123
  -7.500  -0.2485   0.01352   0.00823  -0.1362   0.9341   0.0131
  -7.250  -0.2098   0.01283   0.00742  -0.1388   0.9295   0.0141
  -7.000  -0.1715   0.01217   0.00665  -0.1414   0.9238   0.0153
  -6.750  -0.1337   0.01179   0.00624  -0.1436   0.9167   0.0169
  -6.500  -0.0966   0.01144   0.00579  -0.1457   0.9087   0.0188
  -6.250  -0.0614   0.01101   0.00530  -0.1474   0.8996   0.0207
  -6.000  -0.0291   0.01078   0.00500  -0.1484   0.8898   0.0228
  -5.750   0.0024   0.01058   0.00470  -0.1491   0.8801   0.0249
  -5.500   0.0324   0.01032   0.00436  -0.1496   0.8701   0.0269
  -5.250   0.0623   0.01004   0.00403  -0.1501   0.8612   0.0293
  -5.000   0.0916   0.00988   0.00379  -0.1504   0.8520   0.0315
  -4.750   0.1206   0.00972   0.00356  -0.1507   0.8432   0.0336
  -4.250   0.1792   0.00927   0.00296  -0.1513   0.8262   0.0383
  -4.000   0.2083   0.00910   0.00274  -0.1515   0.8165   0.0413
  -3.750   0.2369   0.00897   0.00253  -0.1516   0.8048   0.0440
  -3.500   0.2654   0.00886   0.00233  -0.1516   0.7928   0.0466
  -3.250   0.2944   0.00873   0.00216  -0.1518   0.7830   0.0524
  -3.000   0.3232   0.00863   0.00203  -0.1519   0.7744   0.0619
  -2.750   0.3523   0.00849   0.00192  -0.1522   0.7660   0.0784
  -2.500   0.3810   0.00841   0.00183  -0.1523   0.7578   0.0939
  -2.250   0.4100   0.00832   0.00174  -0.1525   0.7493   0.1095
  -2.000   0.4390   0.00821   0.00165  -0.1528   0.7412   0.1332
  -1.750   0.4696   0.00784   0.00157  -0.1536   0.7327   0.2381
  -1.500   0.4991   0.00765   0.00157  -0.1541   0.7245   0.3226
  -1.250   0.5283   0.00753   0.00158  -0.1545   0.7158   0.3844
  -0.750   0.5861   0.00740   0.00161  -0.1548   0.6988   0.4624
  -0.500   0.6147   0.00738   0.00166  -0.1549   0.6901   0.4974
  -0.250   0.6430   0.00742   0.00172  -0.1549   0.6815   0.5316
   0.000   0.6713   0.00745   0.00178  -0.1549   0.6721   0.5602
   0.250   0.6993   0.00751   0.00183  -0.1548   0.6628   0.5769
   0.500   0.7272   0.00758   0.00189  -0.1547   0.6530   0.5936
   0.750   0.7548   0.00766   0.00196  -0.1545   0.6405   0.6107
   1.000   0.7819   0.00777   0.00203  -0.1542   0.6237   0.6222
   1.250   0.8087   0.00791   0.00210  -0.1539   0.6039   0.6308
   1.500   0.8357   0.00804   0.00218  -0.1536   0.5856   0.6396
   1.750   0.8628   0.00817   0.00228  -0.1534   0.5696   0.6476
   2.000   0.8890   0.00837   0.00239  -0.1530   0.5451   0.6566
   2.250   0.9145   0.00862   0.00253  -0.1525   0.5121   0.6656
   2.500   0.9394   0.00895   0.00270  -0.1519   0.4746   0.6746
   2.750   0.9649   0.00924   0.00290  -0.1514   0.4467   0.6836
   3.000   0.9909   0.00949   0.00309  -0.1510   0.4259   0.6926
   3.250   1.0170   0.00973   0.00328  -0.1507   0.4082   0.7031
   3.500   1.0429   0.00999   0.00351  -0.1503   0.3856   0.7142
   3.750   1.0679   0.01034   0.00376  -0.1498   0.3560   0.7268
   4.000   1.0919   0.01078   0.00405  -0.1492   0.3170   0.7414
   4.250   1.1150   0.01132   0.00440  -0.1485   0.2716   0.7571
   4.500   1.1384   0.01182   0.00478  -0.1478   0.2351   0.7738
   4.750   1.1620   0.01226   0.00515  -0.1471   0.2077   0.7929
   5.000   1.1851   0.01269   0.00552  -0.1463   0.1832   0.8174
   5.250   1.2065   0.01305   0.00589  -0.1450   0.1600   0.8580
   5.500   1.2222   0.01329   0.00616  -0.1425   0.1380   1.0000
   5.750   1.2455   0.01388   0.00660  -0.1419   0.1115   1.0000
   6.000   1.2684   0.01447   0.00707  -0.1412   0.0903   1.0000
   6.250   1.2921   0.01497   0.00751  -0.1406   0.0785   1.0000
   6.500   1.3159   0.01543   0.00796  -0.1400   0.0696   1.0000
   6.750   1.3392   0.01593   0.00843  -0.1393   0.0612   1.0000
   7.000   1.3621   0.01645   0.00892  -0.1386   0.0524   1.0000
   7.250   1.3851   0.01694   0.00941  -0.1379   0.0470   1.0000
   7.500   1.4073   0.01748   0.00995  -0.1370   0.0428   1.0000
   7.750   1.4297   0.01799   0.01049  -0.1362   0.0404   1.0000
   8.000   1.4516   0.01850   0.01104  -0.1353   0.0388   1.0000
   8.250   1.4729   0.01906   0.01163  -0.1343   0.0374   1.0000
   8.500   1.4932   0.01968   0.01227  -0.1332   0.0354   1.0000
   8.750   1.5117   0.02042   0.01305  -0.1318   0.0329   1.0000
   9.000   1.5321   0.02094   0.01364  -0.1308   0.0320   1.0000
   9.250   1.5513   0.02153   0.01430  -0.1295   0.0308   1.0000
   9.500   1.5692   0.02216   0.01500  -0.1281   0.0296   1.0000
   9.750   1.5844   0.02286   0.01575  -0.1262   0.0284   1.0000
  10.000   1.5972   0.02366   0.01659  -0.1239   0.0271   1.0000
  10.250   1.6069   0.02467   0.01766  -0.1213   0.0258   1.0000
  10.500   1.6225   0.02527   0.01837  -0.1196   0.0251   1.0000
  10.750   1.6369   0.02598   0.01916  -0.1178   0.0240   1.0000
  11.000   1.6503   0.02678   0.02004  -0.1159   0.0226   1.0000
  11.250   1.6627   0.02768   0.02100  -0.1141   0.0212   1.0000
  11.500   1.6731   0.02876   0.02212  -0.1121   0.0197   1.0000
  11.750   1.6848   0.02977   0.02323  -0.1104   0.0184   1.0000
  12.000   1.6956   0.03089   0.02440  -0.1087   0.0164   1.0000
  12.250   1.7049   0.03219   0.02572  -0.1070   0.0145   1.0000
  12.500   1.7126   0.03366   0.02727  -0.1053   0.0131   1.0000
  12.750   1.7191   0.03532   0.02901  -0.1036   0.0118   1.0000
  13.000   1.7240   0.03720   0.03095  -0.1020   0.0107   1.0000
  13.250   1.7287   0.03917   0.03304  -0.1005   0.0100   1.0000
  13.500   1.7322   0.04135   0.03532  -0.0992   0.0094   1.0000
  13.750   1.7342   0.04377   0.03784  -0.0980   0.0088   1.0000
  14.000   1.7346   0.04648   0.04066  -0.0970   0.0083   1.0000
  14.250   1.7345   0.04935   0.04364  -0.0962   0.0080   1.0000
  14.500   1.7346   0.05227   0.04670  -0.0956   0.0077   1.0000
  14.750   1.7338   0.05542   0.04998  -0.0952   0.0074   1.0000
  15.000   1.7316   0.05887   0.05358  -0.0950   0.0071   1.0000
  15.250   1.7283   0.06262   0.05745  -0.0951   0.0068   1.0000
  15.500   1.7238   0.06667   0.06164  -0.0954   0.0066   1.0000
  15.750   1.7176   0.07116   0.06626  -0.0961   0.0063   1.0000
  16.000   1.7102   0.07602   0.07127  -0.0971   0.0062   1.0000
  16.250   1.7008   0.08138   0.07677  -0.0986   0.0060   1.0000
  16.500   1.6891   0.08741   0.08295  -0.1005   0.0059   1.0000
  16.750   1.6797   0.09322   0.08892  -0.1026   0.0058   1.0000
  17.000   1.6688   0.09947   0.09536  -0.1051   0.0057   1.0000
  17.250   1.6570   0.10608   0.10214  -0.1079   0.0056   1.0000
  17.500   1.6436   0.11318   0.10940  -0.1112   0.0056   1.0000
  17.750   1.6310   0.12027   0.11665  -0.1147   0.0055   1.0000
  18.000   1.6160   0.12801   0.12456  -0.1188   0.0054   1.0000
  18.250   1.6006   0.13601   0.13272  -0.1233   0.0054   1.0000
  18.500   1.5857   0.14408   0.14094  -0.1280   0.0053   1.0000
  18.750   1.5704   0.15245   0.14947  -0.1332   0.0054   1.0000
  19.000   1.5553   0.16091   0.15808  -0.1386   0.0053   1.0000
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