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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 200,000
Max Cl/Cd: 84.23 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx601001-il-200000.txt
Download as CSV file: xf-fx601001-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 60-100 (126) 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3815   0.08936   0.08593  -0.0391   1.0000   0.0536
  -8.500  -0.3958   0.08529   0.08196  -0.0433   1.0000   0.0550
  -8.250  -0.4127   0.08160   0.07837  -0.0451   1.0000   0.0553
  -8.000  -0.4316   0.07747   0.07435  -0.0471   1.0000   0.0554
  -7.750  -0.4477   0.07282   0.06970  -0.0521   1.0000   0.0555
  -7.500  -0.4599   0.06892   0.06571  -0.0552   1.0000   0.0555
  -7.000  -0.4702   0.05867   0.05556  -0.0552   1.0000   0.0573
  -6.750  -0.4672   0.05576   0.05265  -0.0549   1.0000   0.0581
  -6.500  -0.4618   0.05260   0.04943  -0.0556   1.0000   0.0592
  -6.250  -0.4161   0.03297   0.02811  -0.0738   0.9966   0.0316
  -6.000  -0.3734   0.02969   0.02410  -0.0789   0.9935   0.0329
  -5.750  -0.3363   0.02542   0.01934  -0.0824   0.9905   0.0324
  -5.500  -0.2973   0.02261   0.01607  -0.0853   0.9873   0.0326
  -5.250  -0.2591   0.01959   0.01274  -0.0879   0.9850   0.0340
  -5.000  -0.2199   0.01836   0.01146  -0.0905   0.9819   0.0378
  -4.750  -0.1837   0.01767   0.01060  -0.0922   0.9765   0.0428
  -4.500  -0.1446   0.01610   0.00907  -0.0948   0.9731   0.0516
  -4.250  -0.1020   0.01483   0.00783  -0.0983   0.9702   0.0781
  -4.000  -0.0653   0.01406   0.00709  -0.1005   0.9644   0.1019
  -3.750  -0.0255   0.01340   0.00656  -0.1034   0.9596   0.1399
  -3.500   0.0172   0.01197   0.00624  -0.1075   0.9568   0.3807
  -3.250   0.0533   0.01225   0.00651  -0.1088   0.9501   0.4566
  -3.000   0.0930   0.01248   0.00662  -0.1108   0.9446   0.4874
  -2.750   0.1364   0.01255   0.00657  -0.1135   0.9413   0.5085
  -2.500   0.1686   0.01258   0.00653  -0.1141   0.9330   0.5245
  -2.250   0.2066   0.01252   0.00649  -0.1156   0.9281   0.5431
  -2.000   0.2382   0.01248   0.00646  -0.1159   0.9198   0.5592
  -1.750   0.2732   0.01237   0.00636  -0.1168   0.9135   0.5751
  -1.500   0.3031   0.01227   0.00623  -0.1168   0.9040   0.5866
  -1.250   0.3375   0.01207   0.00597  -0.1177   0.8974   0.5950
  -1.000   0.3657   0.01192   0.00579  -0.1174   0.8861   0.6008
  -0.750   0.3946   0.01178   0.00563  -0.1172   0.8753   0.6068
  -0.500   0.4243   0.01165   0.00541  -0.1172   0.8644   0.6127
  -0.250   0.4521   0.01148   0.00524  -0.1166   0.8514   0.6182
   0.000   0.4799   0.01140   0.00507  -0.1161   0.8368   0.6262
   0.250   0.5067   0.01131   0.00498  -0.1154   0.8227   0.6326
   0.500   0.5346   0.01129   0.00490  -0.1151   0.8097   0.6390
   0.750   0.5623   0.01126   0.00482  -0.1148   0.7968   0.6435
   1.000   0.5895   0.01125   0.00481  -0.1144   0.7830   0.6478
   1.250   0.6169   0.01125   0.00477  -0.1141   0.7686   0.6522
   1.500   0.6442   0.01125   0.00471  -0.1137   0.7531   0.6568
   1.750   0.6706   0.01124   0.00471  -0.1131   0.7360   0.6613
   2.000   0.6976   0.01126   0.00471  -0.1128   0.7202   0.6662
   2.250   0.7250   0.01131   0.00474  -0.1125   0.7062   0.6712
   2.500   0.7520   0.01135   0.00481  -0.1122   0.6926   0.6765
   2.750   0.7793   0.01143   0.00490  -0.1119   0.6792   0.6829
   3.000   0.8061   0.01151   0.00500  -0.1115   0.6654   0.6886
   3.250   0.8329   0.01160   0.00512  -0.1112   0.6505   0.6956
   3.500   0.8594   0.01169   0.00525  -0.1108   0.6347   0.7034
   3.750   0.8859   0.01180   0.00543  -0.1104   0.6186   0.7132
   4.000   0.9119   0.01190   0.00560  -0.1098   0.6020   0.7234
   4.250   0.9377   0.01202   0.00579  -0.1093   0.5845   0.7363
   4.500   0.9630   0.01215   0.00596  -0.1086   0.5656   0.7541
   4.750   0.9871   0.01220   0.00616  -0.1077   0.5416   0.7820
   5.000   1.0049   0.01193   0.00621  -0.1052   0.5157   1.0000
   5.250   1.0307   0.01224   0.00642  -0.1048   0.4817   1.0000
   5.500   1.0549   0.01261   0.00667  -0.1042   0.4409   1.0000
   5.750   1.0765   0.01319   0.00701  -0.1031   0.3906   1.0000
   6.000   1.0967   0.01396   0.00749  -0.1020   0.3406   1.0000
   6.250   1.1175   0.01473   0.00803  -0.1010   0.2987   1.0000
   6.500   1.1387   0.01546   0.00859  -0.1001   0.2629   1.0000
   6.750   1.1605   0.01613   0.00915  -0.0993   0.2292   1.0000
   7.000   1.1815   0.01687   0.00979  -0.0984   0.1956   1.0000
   7.250   1.1994   0.01799   0.01061  -0.0972   0.1375   1.0000
   7.500   1.2045   0.02075   0.01258  -0.0943   0.0453   1.0000
   7.750   1.2196   0.02224   0.01409  -0.0923   0.0364   1.0000
   8.000   1.2352   0.02352   0.01546  -0.0905   0.0325   1.0000
   8.250   1.2443   0.02541   0.01740  -0.0880   0.0299   1.0000
   8.500   1.2573   0.02697   0.01906  -0.0858   0.0285   1.0000
   8.750   1.2724   0.02827   0.02050  -0.0840   0.0266   1.0000
   9.000   1.2863   0.02968   0.02199  -0.0822   0.0248   1.0000
   9.250   1.2991   0.03137   0.02374  -0.0803   0.0238   1.0000
   9.500   1.3134   0.03336   0.02579  -0.0786   0.0230   1.0000
   9.750   1.3331   0.03612   0.02863  -0.0778   0.0222   1.0000
  10.000   1.3564   0.03977   0.03247  -0.0775   0.0218   1.0000
  10.250   1.3748   0.04342   0.03640  -0.0766   0.0217   1.0000
  10.500   1.3857   0.04767   0.04099  -0.0751   0.0215   1.0000
  10.750   1.3871   0.04927   0.04292  -0.0721   0.0211   1.0000
  11.000   1.3842   0.05134   0.04527  -0.0688   0.0208   1.0000
  11.250   1.3786   0.05388   0.04809  -0.0657   0.0205   1.0000
  11.500   1.3705   0.05709   0.05159  -0.0631   0.0205   1.0000
  11.750   1.3595   0.06097   0.05575  -0.0610   0.0206   1.0000
  12.000   1.3459   0.06531   0.06036  -0.0595   0.0207   1.0000
  12.250   1.3300   0.07008   0.06538  -0.0587   0.0209   1.0000
  12.500   1.3126   0.07574   0.07127  -0.0588   0.0211   1.0000
  13.500   1.1018   0.09949   0.09615  -0.0606   0.0218   1.0000
  13.750   1.0700   0.10682   0.10369  -0.0651   0.0217   1.0000
  14.000   1.0525   0.11272   0.10979  -0.0694   0.0222   1.0000
  14.250   0.9413   0.14151   0.13916  -0.0912   0.0271   1.0000
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