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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 1,000,000
Max Cl/Cd: 96.73 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100-il-1000000-n5.txt
Download as CSV file: xf-fx60100-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 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
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4005   0.09137   0.08971  -0.0369   1.0000   0.0039
  -9.750  -0.4058   0.08633   0.08470  -0.0386   1.0000   0.0039
  -9.000  -0.4760   0.03457   0.03252  -0.0939   0.9721   0.0036
  -8.750  -0.4557   0.02675   0.02409  -0.1060   0.9586   0.0037
  -8.500  -0.4334   0.02377   0.02076  -0.1088   0.9492   0.0038
  -8.250  -0.4093   0.02179   0.01849  -0.1104   0.9412   0.0038
  -8.000  -0.3845   0.02079   0.01730  -0.1109   0.9326   0.0039
  -7.750  -0.3624   0.01795   0.01406  -0.1121   0.9231   0.0040
  -7.500  -0.3381   0.01605   0.01185  -0.1126   0.9138   0.0040
  -7.250  -0.3127   0.01454   0.01011  -0.1130   0.9048   0.0041
  -7.000  -0.2866   0.01331   0.00869  -0.1133   0.8967   0.0042
  -6.750  -0.2597   0.01251   0.00777  -0.1135   0.8883   0.0044
  -6.500  -0.2323   0.01189   0.00703  -0.1137   0.8811   0.0045
  -6.250  -0.2047   0.01134   0.00640  -0.1138   0.8738   0.0047
  -6.000  -0.1768   0.01084   0.00580  -0.1140   0.8675   0.0050
  -5.750  -0.1486   0.01037   0.00525  -0.1142   0.8605   0.0052
  -5.500  -0.1204   0.00996   0.00476  -0.1144   0.8541   0.0055
  -5.250  -0.0919   0.00958   0.00429  -0.1146   0.8474   0.0057
  -5.000  -0.0635   0.00925   0.00388  -0.1148   0.8409   0.0059
  -4.750  -0.0347   0.00893   0.00350  -0.1150   0.8340   0.0061
  -4.500  -0.0062   0.00866   0.00316  -0.1151   0.8270   0.0062
  -4.250   0.0226   0.00837   0.00280  -0.1153   0.8191   0.0065
  -4.000   0.0513   0.00807   0.00241  -0.1155   0.8106   0.0070
  -3.750   0.0800   0.00787   0.00214  -0.1156   0.8016   0.0072
  -3.500   0.1087   0.00770   0.00191  -0.1157   0.7928   0.0075
  -3.250   0.1372   0.00757   0.00172  -0.1157   0.7832   0.0080
  -3.000   0.1658   0.00746   0.00154  -0.1158   0.7716   0.0088
  -2.750   0.1942   0.00736   0.00138  -0.1157   0.7565   0.0124
  -2.500   0.2224   0.00718   0.00121  -0.1158   0.7371   0.0445
  -2.250   0.2505   0.00705   0.00109  -0.1159   0.7149   0.0774
  -2.000   0.2785   0.00696   0.00100  -0.1159   0.6916   0.1124
  -1.750   0.3070   0.00657   0.00088  -0.1164   0.6689   0.2255
  -1.500   0.3354   0.00642   0.00084  -0.1166   0.6515   0.2861
  -1.250   0.3634   0.00644   0.00082  -0.1166   0.6305   0.3098
  -1.000   0.3911   0.00650   0.00083  -0.1166   0.6065   0.3294
  -0.750   0.4187   0.00658   0.00086  -0.1165   0.5793   0.3539
  -0.500   0.4459   0.00672   0.00089  -0.1164   0.5468   0.3748
  -0.250   0.4732   0.00686   0.00094  -0.1163   0.5162   0.3885
   0.000   0.5007   0.00700   0.00100  -0.1162   0.4894   0.4004
   0.250   0.5285   0.00709   0.00105  -0.1161   0.4708   0.4202
   0.500   0.5562   0.00720   0.00112  -0.1161   0.4513   0.4386
   0.750   0.5838   0.00733   0.00119  -0.1160   0.4274   0.4516
   1.000   0.6113   0.00747   0.00128  -0.1160   0.4073   0.4636
   1.250   0.6389   0.00759   0.00137  -0.1159   0.3887   0.4794
   1.500   0.6663   0.00775   0.00147  -0.1158   0.3669   0.4941
   1.750   0.6936   0.00790   0.00158  -0.1157   0.3482   0.5050
   2.000   0.7209   0.00807   0.00170  -0.1156   0.3273   0.5151
   2.250   0.7474   0.00835   0.00185  -0.1154   0.2957   0.5243
   2.500   0.7743   0.00856   0.00199  -0.1153   0.2740   0.5332
   2.750   0.8011   0.00879   0.00215  -0.1151   0.2498   0.5436
   3.000   0.8277   0.00903   0.00233  -0.1149   0.2284   0.5551
   3.250   0.8545   0.00926   0.00250  -0.1147   0.2087   0.5658
   3.500   0.8805   0.00958   0.00272  -0.1145   0.1813   0.5750
   3.750   0.9069   0.00983   0.00292  -0.1143   0.1637   0.5846
   4.000   0.9325   0.01021   0.00318  -0.1140   0.1342   0.5953
   4.250   0.9590   0.01044   0.00340  -0.1138   0.1232   0.6065
   4.500   0.9852   0.01070   0.00363  -0.1135   0.1075   0.6187
   4.750   1.0113   0.01098   0.00388  -0.1133   0.0946   0.6319
   5.000   1.0374   0.01123   0.00414  -0.1130   0.0859   0.6468
   5.250   1.0642   0.01138   0.00435  -0.1129   0.0822   0.6636
   5.500   1.0901   0.01166   0.00463  -0.1126   0.0709   0.6813
   5.750   1.1156   0.01196   0.00494  -0.1123   0.0609   0.7013
   6.250   1.1669   0.01244   0.00555  -0.1116   0.0515   0.7650
   6.500   1.1922   0.01253   0.00584  -0.1112   0.0494   0.8333
   6.750   1.2120   0.01253   0.00607  -0.1095   0.0453   1.0000
   7.000   1.2364   0.01296   0.00647  -0.1090   0.0371   1.0000
   7.250   1.2608   0.01338   0.00684  -0.1085   0.0313   1.0000
   7.500   1.2856   0.01373   0.00719  -0.1081   0.0284   1.0000
   7.750   1.3098   0.01414   0.00759  -0.1076   0.0253   1.0000
   8.000   1.3337   0.01456   0.00800  -0.1070   0.0218   1.0000
   8.250   1.3576   0.01496   0.00842  -0.1065   0.0191   1.0000
   8.500   1.3802   0.01549   0.00893  -0.1058   0.0149   1.0000
   8.750   1.3984   0.01651   0.00985  -0.1045   0.0037   1.0000
   9.000   1.4202   0.01709   0.01048  -0.1036   0.0028   1.0000
   9.250   1.4418   0.01765   0.01109  -0.1027   0.0024   1.0000
   9.500   1.4627   0.01826   0.01175  -0.1017   0.0021   1.0000
   9.750   1.4830   0.01890   0.01246  -0.1007   0.0019   1.0000
  10.000   1.5030   0.01952   0.01315  -0.0996   0.0018   1.0000
  10.250   1.5224   0.02015   0.01385  -0.0984   0.0017   1.0000
  10.500   1.5409   0.02082   0.01459  -0.0971   0.0016   1.0000
  10.750   1.5584   0.02154   0.01538  -0.0957   0.0016   1.0000
  11.000   1.5745   0.02231   0.01622  -0.0941   0.0015   1.0000
  11.250   1.5874   0.02310   0.01710  -0.0920   0.0014   1.0000
  11.500   1.5981   0.02395   0.01802  -0.0895   0.0014   1.0000
  11.750   1.6077   0.02488   0.01904  -0.0870   0.0013   1.0000
  12.000   1.6163   0.02591   0.02016  -0.0846   0.0013   1.0000
  12.500   1.6307   0.02833   0.02279  -0.0799   0.0012   1.0000
  12.750   1.6368   0.02972   0.02427  -0.0777   0.0011   1.0000
  13.000   1.6411   0.03131   0.02597  -0.0756   0.0011   1.0000
  13.250   1.6442   0.03309   0.02786  -0.0736   0.0011   1.0000
  13.500   1.6454   0.03512   0.03002  -0.0717   0.0010   1.0000
  13.750   1.6447   0.03746   0.03249  -0.0701   0.0010   1.0000
  14.000   1.6415   0.04017   0.03534  -0.0686   0.0010   1.0000
  14.250   1.6353   0.04340   0.03871  -0.0675   0.0009   1.0000
  14.500   1.6268   0.04709   0.04257  -0.0668   0.0009   1.0000
  14.750   1.6174   0.05118   0.04681  -0.0666   0.0009   1.0000
  15.000   1.6114   0.05509   0.05085  -0.0669   0.0009   1.0000
  15.250   1.6050   0.05927   0.05517  -0.0677   0.0009   1.0000
  15.500   1.5957   0.06419   0.06023  -0.0690   0.0009   1.0000
  15.750   1.5859   0.06950   0.06568  -0.0707   0.0009   1.0000
  16.000   1.5734   0.07558   0.07190  -0.0731   0.0009   1.0000
  16.250   1.5571   0.08271   0.07920  -0.0763   0.0009   1.0000
  16.500   1.5401   0.09031   0.08696  -0.0800   0.0009   1.0000
  16.750   1.5194   0.09902   0.09583  -0.0845   0.0009   1.0000
  17.000   1.4969   0.10850   0.10548  -0.0896   0.0009   1.0000
  17.250   1.4693   0.11947   0.11662  -0.0957   0.0009   1.0000
  17.500   1.4427   0.13063   0.12795  -0.1022   0.0009   1.0000
  17.750   1.4178   0.14172   0.13920  -0.1087   0.0009   1.0000
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