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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 500,000
Max Cl/Cd: 91.48 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-500000-n5.txt
Download as CSV file: xf-fx60100sm-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX60-100 10.0% smoothed                         
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3855   0.08616   0.08387  -0.0394   1.0000   0.0093
  -9.000  -0.3898   0.08227   0.08003  -0.0403   1.0000   0.0090
  -8.500  -0.4474   0.04343   0.04095  -0.0779   0.9817   0.0071
  -8.250  -0.4232   0.03334   0.03027  -0.0972   0.9720   0.0070
  -8.000  -0.3985   0.02749   0.02384  -0.1044   0.9655   0.0070
  -7.750  -0.3718   0.02359   0.01945  -0.1081   0.9595   0.0070
  -7.500  -0.3416   0.02078   0.01621  -0.1108   0.9555   0.0071
  -7.250  -0.3153   0.01871   0.01381  -0.1118   0.9490   0.0072
  -7.000  -0.2872   0.01680   0.01165  -0.1130   0.9437   0.0074
  -6.750  -0.2585   0.01577   0.01049  -0.1138   0.9387   0.0077
  -6.500  -0.2312   0.01494   0.00953  -0.1140   0.9323   0.0079
  -6.250  -0.2026   0.01418   0.00866  -0.1145   0.9269   0.0083
  -6.000  -0.1752   0.01345   0.00782  -0.1146   0.9204   0.0087
  -5.750  -0.1472   0.01276   0.00702  -0.1148   0.9140   0.0091
  -5.500  -0.1192   0.01215   0.00631  -0.1150   0.9076   0.0095
  -5.250  -0.0912   0.01164   0.00569  -0.1151   0.9005   0.0099
  -5.000  -0.0629   0.01108   0.00505  -0.1154   0.8939   0.0107
  -4.750  -0.0348   0.01067   0.00461  -0.1156   0.8865   0.0116
  -4.500  -0.0063   0.01028   0.00415  -0.1157   0.8796   0.0124
  -4.250   0.0222   0.00991   0.00370  -0.1159   0.8718   0.0133
  -4.000   0.0508   0.00961   0.00331  -0.1160   0.8644   0.0143
  -3.750   0.0794   0.00927   0.00290  -0.1161   0.8563   0.0164
  -3.500   0.1079   0.00906   0.00263  -0.1162   0.8482   0.0189
  -3.250   0.1365   0.00882   0.00234  -0.1162   0.8398   0.0249
  -3.000   0.1653   0.00849   0.00207  -0.1165   0.8310   0.0531
  -2.750   0.1944   0.00776   0.00178  -0.1172   0.8223   0.1866
  -2.500   0.2230   0.00735   0.00164  -0.1176   0.8125   0.2818
  -2.250   0.2514   0.00717   0.00158  -0.1178   0.8026   0.3389
  -2.000   0.2796   0.00708   0.00155  -0.1178   0.7924   0.3838
  -1.750   0.3078   0.00706   0.00150  -0.1177   0.7815   0.4020
  -1.500   0.3360   0.00705   0.00146  -0.1176   0.7700   0.4149
  -1.250   0.3641   0.00705   0.00143  -0.1175   0.7581   0.4285
  -1.000   0.3921   0.00706   0.00141  -0.1174   0.7455   0.4410
  -0.750   0.4201   0.00709   0.00139  -0.1173   0.7324   0.4525
  -0.500   0.4479   0.00713   0.00138  -0.1171   0.7183   0.4638
  -0.250   0.4757   0.00718   0.00139  -0.1170   0.7033   0.4744
   0.000   0.5034   0.00723   0.00140  -0.1168   0.6873   0.4843
   0.250   0.5309   0.00731   0.00142  -0.1166   0.6705   0.4944
   0.500   0.5584   0.00739   0.00146  -0.1165   0.6533   0.5050
   1.000   0.6131   0.00758   0.00157  -0.1161   0.6179   0.5259
   1.250   0.6403   0.00770   0.00164  -0.1159   0.5978   0.5369
   1.500   0.6672   0.00784   0.00173  -0.1156   0.5768   0.5483
   1.750   0.6942   0.00798   0.00183  -0.1154   0.5550   0.5599
   2.000   0.7208   0.00816   0.00194  -0.1151   0.5309   0.5719
   2.250   0.7469   0.00839   0.00207  -0.1148   0.5001   0.5845
   2.500   0.7729   0.00864   0.00222  -0.1144   0.4681   0.5975
   2.750   0.7990   0.00887   0.00238  -0.1141   0.4397   0.6113
   3.000   0.8250   0.00912   0.00255  -0.1138   0.4119   0.6260
   3.250   0.8510   0.00937   0.00274  -0.1135   0.3847   0.6412
   3.500   0.8771   0.00961   0.00295  -0.1132   0.3606   0.6580
   3.750   0.9029   0.00987   0.00317  -0.1128   0.3343   0.6764
   4.000   0.9281   0.01020   0.00342  -0.1124   0.3032   0.6965
   4.250   0.9533   0.01051   0.00368  -0.1120   0.2747   0.7196
   4.500   0.9782   0.01081   0.00397  -0.1116   0.2483   0.7478
   5.000   1.0229   0.01133   0.00456  -0.1095   0.1938   0.8615
   5.250   1.0447   0.01162   0.00483  -0.1083   0.1676   1.0000
   5.750   1.0942   0.01250   0.00554  -0.1075   0.1292   1.0000
   6.000   1.1189   0.01293   0.00590  -0.1071   0.1139   1.0000
   6.250   1.1434   0.01336   0.00629  -0.1066   0.1017   1.0000
   6.500   1.1678   0.01379   0.00669  -0.1061   0.0925   1.0000
   6.750   1.1927   0.01415   0.00707  -0.1057   0.0860   1.0000
   7.000   1.2166   0.01461   0.00750  -0.1051   0.0788   1.0000
   7.250   1.2410   0.01498   0.00790  -0.1046   0.0738   1.0000
   7.500   1.2645   0.01546   0.00837  -0.1040   0.0682   1.0000
   7.750   1.2883   0.01586   0.00881  -0.1035   0.0635   1.0000
   8.000   1.3113   0.01634   0.00928  -0.1028   0.0578   1.0000
   8.250   1.3343   0.01680   0.00977  -0.1021   0.0533   1.0000
   8.500   1.3570   0.01727   0.01025  -0.1014   0.0485   1.0000
   8.750   1.3787   0.01782   0.01082  -0.1006   0.0435   1.0000
   9.000   1.4004   0.01832   0.01134  -0.0998   0.0384   1.0000
   9.250   1.4210   0.01892   0.01194  -0.0988   0.0333   1.0000
   9.500   1.4409   0.01956   0.01258  -0.0978   0.0280   1.0000
   9.750   1.4600   0.02024   0.01327  -0.0966   0.0231   1.0000
  10.000   1.4776   0.02101   0.01405  -0.0953   0.0188   1.0000
  10.250   1.4941   0.02184   0.01491  -0.0937   0.0151   1.0000
  10.500   1.5100   0.02265   0.01578  -0.0921   0.0127   1.0000
  10.750   1.5222   0.02358   0.01674  -0.0900   0.0106   1.0000
  11.000   1.5343   0.02442   0.01767  -0.0878   0.0094   1.0000
  11.250   1.5445   0.02539   0.01871  -0.0854   0.0084   1.0000
  11.500   1.5527   0.02654   0.01994  -0.0830   0.0074   1.0000
  11.750   1.5620   0.02763   0.02114  -0.0808   0.0069   1.0000
  12.000   1.5705   0.02881   0.02243  -0.0787   0.0064   1.0000
  12.250   1.5778   0.03014   0.02385  -0.0766   0.0059   1.0000
  12.500   1.5836   0.03164   0.02547  -0.0746   0.0055   1.0000
  12.750   1.5867   0.03346   0.02739  -0.0726   0.0051   1.0000
  13.000   1.5906   0.03526   0.02932  -0.0708   0.0049   1.0000
  13.250   1.5949   0.03710   0.03129  -0.0693   0.0047   1.0000
  13.500   1.5975   0.03920   0.03352  -0.0680   0.0045   1.0000
  13.750   1.5988   0.04153   0.03598  -0.0668   0.0044   1.0000
  14.000   1.5986   0.04413   0.03873  -0.0659   0.0042   1.0000
  14.250   1.5973   0.04701   0.04174  -0.0653   0.0041   1.0000
  14.500   1.5944   0.05022   0.04509  -0.0650   0.0040   1.0000
  14.750   1.5902   0.05377   0.04879  -0.0650   0.0039   1.0000
  15.000   1.5844   0.05774   0.05290  -0.0655   0.0038   1.0000
  15.250   1.5768   0.06218   0.05750  -0.0664   0.0038   1.0000
  15.500   1.5678   0.06712   0.06259  -0.0678   0.0037   1.0000
  15.750   1.5569   0.07263   0.06826  -0.0697   0.0036   1.0000
  16.000   1.5439   0.07882   0.07462  -0.0722   0.0036   1.0000
  16.250   1.5296   0.08560   0.08157  -0.0752   0.0036   1.0000
  16.500   1.5130   0.09308   0.08922  -0.0788   0.0036   1.0000
  16.750   1.4951   0.10117   0.09748  -0.0830   0.0036   1.0000
  17.000   1.4761   0.10979   0.10627  -0.0876   0.0036   1.0000
  17.250   1.4558   0.11894   0.11560  -0.0927   0.0036   1.0000
  17.500   1.4350   0.12850   0.12532  -0.0981   0.0036   1.0000
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