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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 500,000
Max Cl/Cd: 112.74 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-500000.txt
Download as CSV file: xf-fx60100sm-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.2921   0.09078   0.08861  -0.0408   1.0000   0.0194
  -9.750  -0.2944   0.08665   0.08452  -0.0416   1.0000   0.0194
  -9.500  -0.3080   0.08023   0.07814  -0.0422   1.0000   0.0199
  -9.250  -0.3083   0.07816   0.07611  -0.0407   1.0000   0.0203
  -9.000  -0.3142   0.07564   0.07362  -0.0393   1.0000   0.0205
  -8.750  -0.3235   0.07362   0.07165  -0.0370   1.0000   0.0207
  -8.500  -0.3246   0.07022   0.06827  -0.0376   0.9992   0.0210
  -8.250  -0.3174   0.06498   0.06304  -0.0416   0.9970   0.0214
  -8.000  -0.3108   0.05917   0.05723  -0.0465   0.9944   0.0218
  -7.750  -0.3079   0.05279   0.05086  -0.0521   0.9901   0.0222
  -7.500  -0.3081   0.04336   0.04144  -0.0621   0.9846   0.0225
  -7.250  -0.3062   0.02778   0.02547  -0.0896   0.9757   0.0222
  -7.000  -0.2807   0.02200   0.01935  -0.0984   0.9725   0.0234
  -6.750  -0.2439   0.01981   0.01668  -0.1039   0.9703   0.0262
  -5.750  -0.1512   0.01808   0.01311  -0.1164   0.9607   0.0178
  -5.500  -0.1165   0.01545   0.01014  -0.1179   0.9578   0.0164
  -5.250  -0.0823   0.01408   0.00862  -0.1193   0.9551   0.0167
  -5.000  -0.0555   0.01316   0.00761  -0.1190   0.9483   0.0172
  -4.750  -0.0248   0.01230   0.00667  -0.1195   0.9435   0.0179
  -4.500   0.0047   0.01189   0.00619  -0.1197   0.9384   0.0191
  -4.250   0.0325   0.01093   0.00516  -0.1198   0.9314   0.0202
  -4.000   0.0624   0.01015   0.00431  -0.1202   0.9263   0.0218
  -3.750   0.0900   0.00971   0.00382  -0.1201   0.9186   0.0242
  -3.500   0.1191   0.00929   0.00328  -0.1201   0.9125   0.0276
  -3.250   0.1474   0.00884   0.00281  -0.1201   0.9049   0.0406
  -3.000   0.1769   0.00744   0.00233  -0.1214   0.8984   0.2995
  -2.750   0.2046   0.00722   0.00228  -0.1214   0.8905   0.3675
  -2.500   0.2327   0.00713   0.00220  -0.1212   0.8833   0.4007
  -2.250   0.2604   0.00708   0.00217  -0.1210   0.8746   0.4277
  -2.000   0.2884   0.00705   0.00213  -0.1207   0.8670   0.4527
  -1.750   0.3162   0.00701   0.00208  -0.1205   0.8576   0.4665
  -1.500   0.3442   0.00699   0.00201  -0.1203   0.8488   0.4789
  -1.250   0.3722   0.00698   0.00196  -0.1201   0.8397   0.4919
  -1.000   0.4000   0.00695   0.00193  -0.1199   0.8293   0.5040
  -0.750   0.4279   0.00693   0.00190  -0.1197   0.8192   0.5158
  -0.500   0.4558   0.00692   0.00187  -0.1195   0.8087   0.5276
  -0.250   0.4836   0.00692   0.00185  -0.1193   0.7970   0.5393
   0.000   0.5114   0.00693   0.00184  -0.1191   0.7845   0.5514
   0.250   0.5391   0.00694   0.00184  -0.1189   0.7716   0.5634
   0.500   0.5667   0.00696   0.00185  -0.1186   0.7581   0.5757
   0.750   0.5942   0.00699   0.00187  -0.1184   0.7440   0.5885
   1.000   0.6217   0.00703   0.00190  -0.1181   0.7291   0.6020
   1.250   0.6490   0.00708   0.00194  -0.1179   0.7126   0.6160
   1.500   0.6761   0.00715   0.00200  -0.1176   0.6952   0.6309
   1.750   0.7031   0.00723   0.00206  -0.1173   0.6768   0.6468
   2.000   0.7299   0.00732   0.00213  -0.1169   0.6555   0.6639
   2.250   0.7562   0.00745   0.00221  -0.1165   0.6306   0.6827
   2.500   0.7822   0.00758   0.00233  -0.1160   0.6048   0.7028
   3.000   0.8340   0.00785   0.00258  -0.1150   0.5545   0.7548
   3.250   0.8590   0.00797   0.00273  -0.1144   0.5299   0.7915
   3.500   0.8810   0.00797   0.00287  -0.1130   0.5075   0.8617
   3.750   0.9042   0.00802   0.00296  -0.1119   0.4834   1.0000
   4.000   0.9303   0.00832   0.00313  -0.1116   0.4555   1.0000
   4.250   0.9562   0.00864   0.00333  -0.1113   0.4284   1.0000
   4.500   0.9820   0.00897   0.00356  -0.1109   0.4009   1.0000
   4.750   1.0074   0.00933   0.00380  -0.1106   0.3711   1.0000
   5.000   1.0322   0.00975   0.00407  -0.1101   0.3364   1.0000
   5.250   1.0565   0.01023   0.00439  -0.1096   0.3002   1.0000
   5.500   1.0807   0.01073   0.00473  -0.1091   0.2639   1.0000
   5.750   1.1041   0.01131   0.00512  -0.1085   0.2264   1.0000
   6.000   1.1269   0.01197   0.00557  -0.1079   0.1873   1.0000
   6.250   1.1498   0.01261   0.00605  -0.1072   0.1545   1.0000
   6.500   1.1727   0.01323   0.00654  -0.1065   0.1308   1.0000
   6.750   1.1960   0.01379   0.00703  -0.1059   0.1149   1.0000
   7.000   1.2191   0.01435   0.00755  -0.1052   0.1031   1.0000
   7.250   1.2420   0.01491   0.00807  -0.1045   0.0941   1.0000
   7.500   1.2656   0.01538   0.00859  -0.1039   0.0875   1.0000
   7.750   1.2872   0.01604   0.00920  -0.1030   0.0798   1.0000
   8.000   1.3112   0.01640   0.00964  -0.1024   0.0750   1.0000
   8.250   1.3330   0.01698   0.01019  -0.1016   0.0690   1.0000
   8.500   1.3554   0.01748   0.01074  -0.1008   0.0645   1.0000
   8.750   1.3781   0.01791   0.01121  -0.1001   0.0594   1.0000
   9.000   1.3986   0.01855   0.01186  -0.0991   0.0542   1.0000
   9.250   1.4215   0.01892   0.01229  -0.0985   0.0496   1.0000
   9.500   1.4407   0.01962   0.01297  -0.0973   0.0440   1.0000
   9.750   1.4627   0.02002   0.01342  -0.0966   0.0393   1.0000
  10.000   1.4811   0.02072   0.01412  -0.0953   0.0335   1.0000
  10.250   1.4974   0.02159   0.01496  -0.0938   0.0265   1.0000
  10.500   1.5123   0.02251   0.01590  -0.0920   0.0209   1.0000
  10.750   1.5231   0.02356   0.01700  -0.0896   0.0170   1.0000
  11.000   1.5274   0.02499   0.01848  -0.0863   0.0143   1.0000
  11.250   1.5367   0.02605   0.01965  -0.0838   0.0129   1.0000
  11.500   1.5434   0.02733   0.02101  -0.0813   0.0117   1.0000
  11.750   1.5419   0.02929   0.02307  -0.0780   0.0106   1.0000
  12.000   1.5455   0.03093   0.02485  -0.0756   0.0101   1.0000
  12.250   1.5513   0.03247   0.02652  -0.0736   0.0095   1.0000
  12.500   1.5551   0.03424   0.02841  -0.0717   0.0090   1.0000
  12.750   1.5575   0.03623   0.03052  -0.0700   0.0086   1.0000
  13.000   1.5577   0.03853   0.03294  -0.0684   0.0083   1.0000
  13.250   1.5556   0.04119   0.03573  -0.0670   0.0080   1.0000
  13.500   1.5501   0.04437   0.03905  -0.0659   0.0078   1.0000
  13.750   1.5411   0.04819   0.04301  -0.0652   0.0076   1.0000
  14.000   1.5292   0.05264   0.04763  -0.0650   0.0075   1.0000
  14.250   1.5152   0.05768   0.05284  -0.0653   0.0073   1.0000
  14.500   1.5099   0.06180   0.05711  -0.0660   0.0073   1.0000
  14.750   1.5038   0.06626   0.06174  -0.0671   0.0072   1.0000
  15.000   1.4958   0.07123   0.06688  -0.0686   0.0071   1.0000
  15.250   1.4869   0.07660   0.07241  -0.0705   0.0071   1.0000
  15.500   1.4769   0.08241   0.07839  -0.0728   0.0070   1.0000
  15.750   1.4657   0.08866   0.08480  -0.0755   0.0070   1.0000
  16.000   1.4534   0.09534   0.09165  -0.0787   0.0069   1.0000
  16.250   1.4411   0.10230   0.09877  -0.0821   0.0069   1.0000
  16.500   1.4275   0.10968   0.10631  -0.0860   0.0069   1.0000
  16.750   1.4142   0.11726   0.11405  -0.0901   0.0068   1.0000
  17.000   1.4006   0.12510   0.12205  -0.0946   0.0068   1.0000
  17.250   1.3871   0.13311   0.13020  -0.0993   0.0068   1.0000
  17.500   1.3730   0.14141   0.13865  -0.1043   0.0068   1.0000
  17.750   1.3592   0.14990   0.14729  -0.1096   0.0069   1.0000
  18.000   1.3462   0.15849   0.15602  -0.1152   0.0068   1.0000
  18.250   1.3324   0.16748   0.16515  -0.1211   0.0069   1.0000
  18.500   1.3184   0.17676   0.17457  -0.1272   0.0069   1.0000
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