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FX 60-100 (126) AIRFOIL (fx601001-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 60-100 (126) AIRFOIL (fx601001-il)
Reynolds number: 200,000
Max Cl/Cd: 76.76 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx601001-il-200000-n5.txt
Download as CSV file: xf-fx601001-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3889   0.08645   0.08297  -0.0399   1.0000   0.0118
  -9.000  -0.3939   0.08212   0.07870  -0.0412   1.0000   0.0117
  -8.750  -0.4017   0.07756   0.07421  -0.0424   1.0000   0.0116
  -8.500  -0.4131   0.07309   0.06983  -0.0433   1.0000   0.0115
  -8.250  -0.4297   0.06877   0.06561  -0.0434   1.0000   0.0114
  -8.000  -0.4525   0.06499   0.06193  -0.0421   1.0000   0.0112
  -7.750  -0.4652   0.05266   0.04954  -0.0556   0.9957   0.0109
  -7.500  -0.4342   0.03784   0.03392  -0.0819   0.9843   0.0108
  -7.250  -0.3997   0.03138   0.02676  -0.0909   0.9780   0.0110
  -7.000  -0.3656   0.02837   0.02328  -0.0951   0.9725   0.0118
  -6.750  -0.3313   0.02398   0.01821  -0.0995   0.9683   0.0126
  -6.500  -0.2956   0.02091   0.01467  -0.1027   0.9657   0.0131
  -6.250  -0.2653   0.01892   0.01241  -0.1040   0.9602   0.0139
  -6.000  -0.2312   0.01747   0.01072  -0.1058   0.9563   0.0148
  -5.750  -0.1956   0.01633   0.00942  -0.1079   0.9532   0.0163
  -5.500  -0.1652   0.01557   0.00854  -0.1087   0.9470   0.0190
  -5.250  -0.1312   0.01472   0.00753  -0.1102   0.9421   0.0213
  -5.000  -0.0955   0.01390   0.00664  -0.1121   0.9382   0.0261
  -4.750  -0.0657   0.01338   0.00612  -0.1127   0.9305   0.0411
  -4.500  -0.0320   0.01294   0.00564  -0.1140   0.9256   0.0581
  -4.250  -0.0020   0.01258   0.00524  -0.1146   0.9180   0.0721
  -4.000   0.0306   0.01212   0.00482  -0.1158   0.9119   0.0953
  -3.750   0.0608   0.01161   0.00443  -0.1165   0.9036   0.1339
  -3.500   0.0932   0.01095   0.00406  -0.1179   0.8969   0.2245
  -3.250   0.1229   0.01050   0.00380  -0.1185   0.8882   0.2975
  -3.000   0.1535   0.01025   0.00378  -0.1190   0.8807   0.3807
  -2.750   0.1825   0.01026   0.00380  -0.1190   0.8712   0.4271
  -2.500   0.2117   0.01033   0.00379  -0.1189   0.8617   0.4558
  -2.250   0.2412   0.01040   0.00373  -0.1190   0.8527   0.4754
  -2.000   0.2699   0.01048   0.00370  -0.1188   0.8427   0.4917
  -1.750   0.2982   0.01055   0.00370  -0.1186   0.8323   0.5070
  -1.500   0.3263   0.01056   0.00366  -0.1184   0.8220   0.5174
  -1.000   0.3827   0.01053   0.00349  -0.1181   0.8002   0.5277
  -0.750   0.4108   0.01055   0.00342  -0.1180   0.7887   0.5328
  -0.500   0.4386   0.01055   0.00337  -0.1178   0.7770   0.5381
  -0.250   0.4661   0.01057   0.00333  -0.1175   0.7629   0.5439
   0.000   0.4935   0.01060   0.00328  -0.1172   0.7458   0.5499
   0.250   0.5204   0.01062   0.00325  -0.1168   0.7284   0.5546
   0.500   0.5478   0.01066   0.00324  -0.1166   0.7135   0.5591
   0.750   0.5754   0.01072   0.00324  -0.1164   0.6995   0.5630
   1.000   0.6028   0.01077   0.00325  -0.1162   0.6857   0.5658
   1.250   0.6299   0.01083   0.00328  -0.1159   0.6704   0.5686
   1.500   0.6568   0.01092   0.00332  -0.1155   0.6532   0.5720
   1.750   0.6835   0.01104   0.00337  -0.1152   0.6342   0.5756
   2.000   0.7103   0.01116   0.00344  -0.1149   0.6167   0.5788
   2.250   0.7371   0.01126   0.00356  -0.1146   0.6025   0.5818
   2.500   0.7639   0.01139   0.00369  -0.1143   0.5890   0.5855
   2.750   0.7907   0.01152   0.00383  -0.1140   0.5753   0.5897
   3.000   0.8175   0.01167   0.00400  -0.1138   0.5622   0.5938
   3.250   0.8441   0.01181   0.00418  -0.1135   0.5489   0.5977
   3.500   0.8707   0.01196   0.00437  -0.1132   0.5346   0.6023
   4.000   0.9231   0.01230   0.00483  -0.1125   0.4993   0.6138
   4.250   0.9487   0.01251   0.00506  -0.1120   0.4779   0.6209
   4.500   0.9742   0.01271   0.00532  -0.1115   0.4530   0.6284
   4.750   0.9986   0.01301   0.00559  -0.1109   0.4211   0.6379
   5.000   1.0217   0.01341   0.00596  -0.1101   0.3834   0.6499
   5.250   1.0439   0.01393   0.00637  -0.1092   0.3466   0.6658
   5.500   1.0665   0.01441   0.00683  -0.1084   0.3161   0.6872
   5.750   1.0878   0.01498   0.00734  -0.1074   0.2791   0.7170
   6.250   1.1227   0.01592   0.00827  -0.1038   0.1991   1.0000
   6.500   1.1446   0.01663   0.00885  -0.1031   0.1705   1.0000
   6.750   1.1654   0.01745   0.00955  -0.1022   0.1354   1.0000
   7.000   1.1825   0.01871   0.01042  -0.1010   0.0779   1.0000
   7.250   1.1971   0.02026   0.01164  -0.0994   0.0320   1.0000
   7.500   1.2144   0.02148   0.01278  -0.0980   0.0192   1.0000
   7.750   1.2341   0.02239   0.01381  -0.0967   0.0168   1.0000
   8.000   1.2526   0.02336   0.01493  -0.0954   0.0150   1.0000
   8.250   1.2694   0.02444   0.01613  -0.0939   0.0132   1.0000
   8.500   1.2832   0.02576   0.01759  -0.0920   0.0117   1.0000
   8.750   1.2926   0.02737   0.01938  -0.0896   0.0110   1.0000
   9.000   1.2963   0.02927   0.02145  -0.0864   0.0104   1.0000
   9.250   1.3034   0.03078   0.02307  -0.0837   0.0102   1.0000
   9.500   1.3105   0.03233   0.02475  -0.0812   0.0099   1.0000
   9.750   1.3173   0.03402   0.02658  -0.0789   0.0097   1.0000
  10.000   1.3243   0.03575   0.02845  -0.0767   0.0093   1.0000
  10.250   1.3313   0.03751   0.03043  -0.0748   0.0088   1.0000
  10.500   1.3376   0.03937   0.03243  -0.0730   0.0083   1.0000
  10.750   1.3430   0.04135   0.03456  -0.0714   0.0079   1.0000
  11.000   1.3470   0.04361   0.03697  -0.0699   0.0076   1.0000
  11.250   1.3500   0.04611   0.03963  -0.0685   0.0075   1.0000
  11.500   1.3517   0.04880   0.04249  -0.0673   0.0073   1.0000
  11.750   1.3521   0.05173   0.04558  -0.0663   0.0071   1.0000
  12.000   1.3509   0.05493   0.04897  -0.0656   0.0070   1.0000
  12.250   1.3482   0.05844   0.05266  -0.0651   0.0069   1.0000
  12.500   1.3438   0.06230   0.05671  -0.0650   0.0068   1.0000
  12.750   1.3374   0.06656   0.06118  -0.0652   0.0067   1.0000
  13.000   1.3290   0.07126   0.06608  -0.0659   0.0067   1.0000
  13.250   1.3191   0.07638   0.07141  -0.0671   0.0066   1.0000
  13.500   1.3077   0.08192   0.07718  -0.0688   0.0066   1.0000
  13.750   1.2949   0.08794   0.08341  -0.0712   0.0066   1.0000
  14.000   1.2819   0.09432   0.09000  -0.0741   0.0066   1.0000
  14.250   1.2679   0.10121   0.09710  -0.0776   0.0066   1.0000
  14.500   1.2540   0.10853   0.10462  -0.0817   0.0066   1.0000
  14.750   1.2397   0.11641   0.11269  -0.0864   0.0066   1.0000
  15.000   1.2256   0.12471   0.12119  -0.0917   0.0066   1.0000
  15.250   1.2113   0.13367   0.13034  -0.0976   0.0067   1.0000
  15.500   1.1953   0.14368   0.14054  -0.1043   0.0068   1.0000
  15.750   1.1755   0.15583   0.15290  -0.1125   0.0069   1.0000
  16.000   1.1390   0.17573   0.17304  -0.1252   0.0073   1.0000
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