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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.65 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-1000000-n5.txt
Download as CSV file: xf-fx60100sm-il-1000000-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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.4126   0.08590   0.08424  -0.0392   1.0000   0.0052
  -9.250  -0.5121   0.03024   0.02781  -0.0996   0.9723   0.0047
  -9.000  -0.4909   0.02425   0.02126  -0.1072   0.9625   0.0047
  -8.750  -0.4677   0.02037   0.01689  -0.1107   0.9545   0.0048
  -8.500  -0.4455   0.01761   0.01373  -0.1120   0.9458   0.0048
  -8.250  -0.4205   0.01577   0.01160  -0.1129   0.9391   0.0049
  -8.000  -0.3951   0.01446   0.01010  -0.1133   0.9320   0.0050
  -7.750  -0.3685   0.01358   0.00906  -0.1136   0.9259   0.0051
  -7.500  -0.3416   0.01290   0.00828  -0.1138   0.9192   0.0053
  -7.250  -0.3145   0.01235   0.00763  -0.1139   0.9128   0.0054
  -7.000  -0.2870   0.01184   0.00704  -0.1141   0.9063   0.0056
  -6.750  -0.2595   0.01135   0.00646  -0.1142   0.8994   0.0058
  -6.500  -0.2318   0.01087   0.00589  -0.1144   0.8928   0.0061
  -6.250  -0.2039   0.01045   0.00538  -0.1145   0.8854   0.0064
  -6.000  -0.1759   0.01005   0.00490  -0.1147   0.8784   0.0066
  -5.750  -0.1477   0.00969   0.00446  -0.1148   0.8708   0.0069
  -5.500  -0.1195   0.00938   0.00408  -0.1149   0.8636   0.0070
  -5.250  -0.0911   0.00900   0.00360  -0.1151   0.8557   0.0073
  -5.000  -0.0625   0.00866   0.00320  -0.1153   0.8480   0.0078
  -4.750  -0.0342   0.00843   0.00292  -0.1154   0.8398   0.0082
  -4.500  -0.0057   0.00823   0.00268  -0.1155   0.8314   0.0089
  -4.250   0.0227   0.00808   0.00246  -0.1156   0.8230   0.0097
  -4.000   0.0513   0.00788   0.00221  -0.1157   0.8138   0.0107
  -3.750   0.0799   0.00770   0.00198  -0.1158   0.8048   0.0122
  -3.500   0.1083   0.00758   0.00180  -0.1158   0.7951   0.0137
  -3.250   0.1369   0.00745   0.00163  -0.1159   0.7848   0.0161
  -3.000   0.1654   0.00734   0.00149  -0.1159   0.7743   0.0199
  -2.750   0.1940   0.00717   0.00133  -0.1161   0.7634   0.0375
  -2.500   0.2229   0.00673   0.00113  -0.1165   0.7517   0.1267
  -2.250   0.2518   0.00632   0.00099  -0.1170   0.7395   0.2229
  -2.000   0.2804   0.00613   0.00092  -0.1172   0.7270   0.2816
  -1.750   0.3088   0.00602   0.00089  -0.1174   0.7138   0.3292
  -1.500   0.3370   0.00596   0.00088  -0.1174   0.6999   0.3648
  -1.250   0.3652   0.00598   0.00086  -0.1174   0.6851   0.3792
  -1.000   0.3933   0.00603   0.00086  -0.1173   0.6694   0.3909
  -0.750   0.4212   0.00608   0.00086  -0.1173   0.6529   0.4040
  -0.500   0.4491   0.00615   0.00088  -0.1172   0.6357   0.4163
  -0.250   0.4771   0.00621   0.00090  -0.1171   0.6184   0.4272
   0.000   0.5050   0.00628   0.00093  -0.1171   0.6011   0.4379
   0.500   0.5605   0.00648   0.00102  -0.1169   0.5637   0.4569
   0.750   0.5881   0.00659   0.00107  -0.1168   0.5430   0.4660
   1.000   0.6156   0.00673   0.00114  -0.1167   0.5217   0.4756
   1.250   0.6431   0.00686   0.00121  -0.1166   0.5013   0.4852
   1.500   0.6701   0.00704   0.00131  -0.1164   0.4748   0.4945
   1.750   0.6969   0.00726   0.00142  -0.1162   0.4423   0.5048
   2.000   0.7237   0.00748   0.00154  -0.1160   0.4118   0.5147
   2.250   0.7504   0.00770   0.00166  -0.1158   0.3838   0.5248
   2.500   0.7772   0.00793   0.00181  -0.1156   0.3564   0.5358
   2.750   0.8041   0.00813   0.00194  -0.1155   0.3336   0.5471
   3.000   0.8309   0.00833   0.00210  -0.1153   0.3118   0.5587
   3.250   0.8572   0.00861   0.00227  -0.1151   0.2830   0.5703
   3.500   0.8834   0.00889   0.00247  -0.1149   0.2566   0.5825
   3.750   0.9098   0.00914   0.00267  -0.1146   0.2339   0.5959
   4.000   0.9360   0.00941   0.00288  -0.1144   0.2117   0.6095
   4.250   0.9618   0.00973   0.00311  -0.1141   0.1862   0.6238
   4.500   0.9873   0.01008   0.00339  -0.1138   0.1601   0.6395
   4.750   1.0132   0.01036   0.00364  -0.1135   0.1416   0.6560
   5.000   1.0391   0.01064   0.00390  -0.1132   0.1256   0.6738
   5.250   1.0648   0.01093   0.00418  -0.1129   0.1113   0.6953
   5.500   1.0904   0.01120   0.00446  -0.1126   0.0987   0.7192
   5.750   1.1162   0.01144   0.00474  -0.1123   0.0901   0.7485
   6.000   1.1417   0.01164   0.00503  -0.1119   0.0832   0.7906
   6.250   1.1615   0.01154   0.00526  -0.1102   0.0776   1.0000
   6.500   1.1870   0.01185   0.00555  -0.1098   0.0716   1.0000
   6.750   1.2124   0.01216   0.00585  -0.1095   0.0664   1.0000
   7.000   1.2379   0.01245   0.00615  -0.1091   0.0624   1.0000
   7.250   1.2625   0.01285   0.00650  -0.1087   0.0556   1.0000
   7.500   1.2876   0.01315   0.00682  -0.1083   0.0517   1.0000
   7.750   1.3116   0.01357   0.00720  -0.1077   0.0453   1.0000
   8.000   1.3360   0.01393   0.00755  -0.1073   0.0406   1.0000
   8.250   1.3593   0.01440   0.00798  -0.1066   0.0348   1.0000
   8.500   1.3832   0.01478   0.00838  -0.1061   0.0315   1.0000
   8.750   1.4057   0.01528   0.00886  -0.1054   0.0263   1.0000
   9.000   1.4283   0.01578   0.00935  -0.1046   0.0221   1.0000
   9.250   1.4499   0.01634   0.00990  -0.1038   0.0177   1.0000
   9.500   1.4707   0.01696   0.01051  -0.1028   0.0138   1.0000
   9.750   1.4910   0.01760   0.01115  -0.1018   0.0109   1.0000
  10.000   1.5114   0.01820   0.01179  -0.1008   0.0089   1.0000
  10.250   1.5306   0.01887   0.01249  -0.0996   0.0072   1.0000
  10.500   1.5497   0.01951   0.01316  -0.0984   0.0061   1.0000
  10.750   1.5673   0.02024   0.01393  -0.0970   0.0051   1.0000
  11.000   1.5851   0.02088   0.01463  -0.0956   0.0046   1.0000
  11.250   1.6017   0.02158   0.01538  -0.0940   0.0042   1.0000
  11.500   1.6148   0.02232   0.01618  -0.0919   0.0038   1.0000
  11.750   1.6256   0.02314   0.01706  -0.0895   0.0035   1.0000
  12.000   1.6353   0.02404   0.01804  -0.0870   0.0032   1.0000
  12.250   1.6460   0.02490   0.01898  -0.0847   0.0031   1.0000
  12.500   1.6557   0.02586   0.02002  -0.0825   0.0030   1.0000
  12.750   1.6647   0.02691   0.02116  -0.0804   0.0029   1.0000
  13.000   1.6728   0.02808   0.02242  -0.0783   0.0028   1.0000
  13.250   1.6801   0.02936   0.02379  -0.0763   0.0027   1.0000
  13.500   1.6866   0.03076   0.02528  -0.0744   0.0026   1.0000
  13.750   1.6922   0.03230   0.02691  -0.0726   0.0025   1.0000
  14.000   1.6967   0.03400   0.02871  -0.0709   0.0024   1.0000
  14.250   1.7002   0.03588   0.03069  -0.0694   0.0024   1.0000
  14.500   1.7024   0.03798   0.03289  -0.0681   0.0023   1.0000
  14.750   1.7031   0.04033   0.03535  -0.0669   0.0022   1.0000
  15.000   1.7023   0.04295   0.03809  -0.0660   0.0022   1.0000
  15.250   1.6996   0.04595   0.04121  -0.0653   0.0021   1.0000
  15.500   1.6956   0.04926   0.04465  -0.0650   0.0021   1.0000
  15.750   1.6892   0.05307   0.04859  -0.0651   0.0020   1.0000
  16.000   1.6808   0.05737   0.05304  -0.0656   0.0020   1.0000
  16.250   1.6709   0.06217   0.05799  -0.0666   0.0020   1.0000
  16.500   1.6584   0.06770   0.06367  -0.0683   0.0019   1.0000
  16.750   1.6444   0.07378   0.06991  -0.0705   0.0019   1.0000
  17.000   1.6297   0.08035   0.07663  -0.0733   0.0019   1.0000
  17.250   1.6142   0.08737   0.08381  -0.0765   0.0019   1.0000
  17.500   1.5948   0.09543   0.09203  -0.0805   0.0019   1.0000
  17.750   1.5727   0.10442   0.10119  -0.0852   0.0019   1.0000
  18.000   1.5500   0.11384   0.11077  -0.0903   0.0019   1.0000
  18.250   1.5230   0.12451   0.12162  -0.0964   0.0019   1.0000
  18.500   1.4982   0.13502   0.13229  -0.1026   0.0019   1.0000
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