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FX 60-100 AIRFOIL (fx60100-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: FX 60-100 AIRFOIL (fx60100-il)
Reynolds number: 1,000,000
Max Cl/Cd: 112.4 at α=3.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100-il-1000000.txt
Download as CSV file: xf-fx60100-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.2842   0.10478   0.10320  -0.0359   1.0000   0.0080
 -10.750  -0.2848   0.10054   0.09897  -0.0368   1.0000   0.0087
 -10.500  -0.2853   0.09574   0.09419  -0.0380   1.0000   0.0093
  -5.750  -0.1402   0.01350   0.00894  -0.1165   0.9189   0.0098
  -5.500  -0.1133   0.01189   0.00721  -0.1164   0.9128   0.0089
  -5.250  -0.0856   0.01088   0.00609  -0.1165   0.9060   0.0090
  -5.000  -0.0576   0.01030   0.00541  -0.1165   0.8998   0.0093
  -4.750  -0.0293   0.00969   0.00471  -0.1166   0.8933   0.0096
  -4.500  -0.0007   0.00887   0.00377  -0.1169   0.8867   0.0100
  -4.250   0.0281   0.00839   0.00321  -0.1172   0.8799   0.0104
  -4.000   0.0567   0.00806   0.00279  -0.1173   0.8726   0.0110
  -3.750   0.0854   0.00779   0.00247  -0.1174   0.8657   0.0116
  -3.500   0.1142   0.00756   0.00216  -0.1174   0.8583   0.0120
  -3.250   0.1430   0.00738   0.00191  -0.1175   0.8512   0.0125
  -3.000   0.1716   0.00723   0.00168  -0.1174   0.8431   0.0137
  -2.750   0.2009   0.00672   0.00138  -0.1178   0.8338   0.0825
  -2.500   0.2298   0.00617   0.00117  -0.1183   0.8234   0.2016
  -2.250   0.2583   0.00584   0.00105  -0.1186   0.8122   0.2877
  -2.000   0.2868   0.00569   0.00099  -0.1187   0.8007   0.3336
  -1.750   0.3153   0.00556   0.00098  -0.1188   0.7898   0.3869
  -1.500   0.3436   0.00554   0.00095  -0.1188   0.7800   0.4083
  -1.250   0.3719   0.00555   0.00093  -0.1188   0.7684   0.4219
  -0.750   0.4280   0.00559   0.00090  -0.1186   0.7380   0.4473
  -0.500   0.4558   0.00564   0.00090  -0.1184   0.7172   0.4604
  -0.250   0.4833   0.00572   0.00091  -0.1182   0.6938   0.4715
   0.000   0.5109   0.00582   0.00093  -0.1181   0.6714   0.4823
   0.250   0.5385   0.00591   0.00097  -0.1179   0.6510   0.4968
   0.500   0.5660   0.00601   0.00102  -0.1178   0.6278   0.5113
   0.750   0.5934   0.00613   0.00108  -0.1176   0.6048   0.5230
   1.000   0.6208   0.00626   0.00115  -0.1175   0.5833   0.5352
   1.250   0.6483   0.00638   0.00123  -0.1174   0.5627   0.5493
   1.500   0.6758   0.00650   0.00132  -0.1173   0.5431   0.5626
   1.750   0.7032   0.00664   0.00140  -0.1171   0.5244   0.5741
   2.000   0.7306   0.00678   0.00151  -0.1170   0.5024   0.5857
   2.250   0.7576   0.00696   0.00161  -0.1168   0.4785   0.5971
   2.500   0.7848   0.00712   0.00173  -0.1167   0.4562   0.6084
   2.750   0.8119   0.00730   0.00185  -0.1165   0.4329   0.6208
   3.000   0.8387   0.00750   0.00200  -0.1164   0.4091   0.6341
   3.250   0.8655   0.00770   0.00215  -0.1162   0.3837   0.6479
   3.500   0.8918   0.00795   0.00232  -0.1159   0.3548   0.6625
   3.750   0.9180   0.00821   0.00251  -0.1157   0.3269   0.6795
   4.000   0.9434   0.00857   0.00275  -0.1154   0.2886   0.6996
   4.250   0.9691   0.00886   0.00299  -0.1151   0.2573   0.7256
   4.500   0.9942   0.00920   0.00326  -0.1147   0.2238   0.7627
   4.750   1.0180   0.00947   0.00357  -0.1140   0.1889   0.8336
   5.000   1.0373   0.00960   0.00380  -0.1122   0.1632   1.0000
   5.250   1.0624   0.01004   0.00410  -0.1118   0.1365   1.0000
   5.500   1.0883   0.01037   0.00437  -0.1116   0.1240   1.0000
   5.750   1.1141   0.01070   0.00465  -0.1113   0.1096   1.0000
   6.000   1.1393   0.01109   0.00496  -0.1109   0.0952   1.0000
   6.250   1.1646   0.01146   0.00528  -0.1105   0.0856   1.0000
   6.500   1.1900   0.01180   0.00559  -0.1102   0.0743   1.0000
   6.750   1.2145   0.01224   0.00594  -0.1097   0.0618   1.0000
   7.000   1.2391   0.01264   0.00632  -0.1093   0.0562   1.0000
   7.250   1.2638   0.01304   0.00670  -0.1088   0.0506   1.0000
   7.500   1.2894   0.01329   0.00701  -0.1085   0.0477   1.0000
   7.750   1.3131   0.01377   0.00745  -0.1079   0.0397   1.0000
   8.000   1.3371   0.01418   0.00784  -0.1074   0.0351   1.0000
   8.250   1.3604   0.01466   0.00828  -0.1068   0.0298   1.0000
   8.500   1.3843   0.01505   0.00870  -0.1062   0.0274   1.0000
   8.750   1.4068   0.01558   0.00920  -0.1055   0.0231   1.0000
   9.000   1.4295   0.01604   0.00966  -0.1048   0.0181   1.0000
   9.250   1.4456   0.01723   0.01070  -0.1032   0.0054   1.0000
   9.500   1.4661   0.01791   0.01144  -0.1021   0.0042   1.0000
   9.750   1.4856   0.01863   0.01223  -0.1009   0.0037   1.0000
  10.000   1.5039   0.01946   0.01315  -0.0995   0.0032   1.0000
  10.250   1.5218   0.02027   0.01406  -0.0981   0.0030   1.0000
  10.500   1.5393   0.02106   0.01494  -0.0966   0.0029   1.0000
  10.750   1.5552   0.02193   0.01590  -0.0949   0.0028   1.0000
  11.000   1.5690   0.02285   0.01691  -0.0930   0.0027   1.0000
  11.250   1.5790   0.02380   0.01796  -0.0904   0.0026   1.0000
  11.500   1.5869   0.02484   0.01910  -0.0876   0.0025   1.0000
  11.750   1.5938   0.02599   0.02035  -0.0848   0.0025   1.0000
  12.000   1.5998   0.02725   0.02172  -0.0822   0.0024   1.0000
  12.250   1.6045   0.02868   0.02325  -0.0796   0.0023   1.0000
  12.500   1.6081   0.03026   0.02495  -0.0772   0.0023   1.0000
  12.750   1.6108   0.03200   0.02680  -0.0750   0.0022   1.0000
  13.000   1.6112   0.03403   0.02896  -0.0729   0.0022   1.0000
  13.250   1.6097   0.03636   0.03142  -0.0710   0.0021   1.0000
  13.500   1.6065   0.03901   0.03420  -0.0693   0.0021   1.0000
  13.750   1.6015   0.04201   0.03734  -0.0681   0.0020   1.0000
  14.000   1.5949   0.04540   0.04088  -0.0672   0.0020   1.0000
  14.250   1.5870   0.04919   0.04481  -0.0668   0.0020   1.0000
  14.500   1.5778   0.05343   0.04920  -0.0670   0.0020   1.0000
  14.750   1.5673   0.05815   0.05407  -0.0677   0.0020   1.0000
  15.000   1.5552   0.06346   0.05953  -0.0691   0.0020   1.0000
  15.250   1.5422   0.06931   0.06553  -0.0710   0.0020   1.0000
  15.500   1.5286   0.07562   0.07200  -0.0735   0.0020   1.0000
  15.750   1.5142   0.08243   0.07896  -0.0766   0.0020   1.0000
  16.000   1.4986   0.08981   0.08649  -0.0801   0.0020   1.0000
  16.250   1.4819   0.09771   0.09454  -0.0841   0.0020   1.0000
  16.500   1.4651   0.10594   0.10292  -0.0884   0.0020   1.0000
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