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FX60-100 10.0% smoothed (fx60100sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX60-100 10.0% smoothed (fx60100sm-il)
Reynolds number: 200,000
Max Cl/Cd: 79.11 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx60100sm-il-200000-n5.txt
Download as CSV file: xf-fx60100sm-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2974   0.08509   0.08171  -0.0400   1.0000   0.0182
  -9.250  -0.3744   0.09103   0.08742  -0.0395   1.0000   0.0185
  -9.000  -0.3748   0.08786   0.08430  -0.0399   1.0000   0.0179
  -8.750  -0.3778   0.08433   0.08080  -0.0405   1.0000   0.0172
  -8.250  -0.4206   0.06939   0.06604  -0.0441   1.0000   0.0141
  -8.000  -0.4405   0.06689   0.06364  -0.0418   1.0000   0.0140
  -7.750  -0.4354   0.05735   0.05405  -0.0547   0.9928   0.0137
  -7.500  -0.4109   0.04530   0.04154  -0.0776   0.9831   0.0134
  -7.250  -0.3878   0.03876   0.03453  -0.0866   0.9755   0.0132
  -7.000  -0.3566   0.03327   0.02846  -0.0936   0.9712   0.0131
  -6.750  -0.3246   0.02912   0.02375  -0.0980   0.9673   0.0131
  -6.500  -0.2939   0.02604   0.02016  -0.1007   0.9624   0.0133
  -6.250  -0.2595   0.02353   0.01716  -0.1032   0.9592   0.0137
  -6.000  -0.2237   0.02172   0.01495  -0.1055   0.9567   0.0141
  -5.750  -0.1918   0.02004   0.01317  -0.1072   0.9532   0.0152
  -5.500  -0.1620   0.01912   0.01214  -0.1081   0.9479   0.0165
  -5.250  -0.1288   0.01791   0.01077  -0.1094   0.9441   0.0173
  -5.000  -0.0942   0.01677   0.00951  -0.1109   0.9411   0.0179
  -4.750  -0.0653   0.01589   0.00854  -0.1112   0.9348   0.0187
  -4.500  -0.0329   0.01502   0.00760  -0.1123   0.9299   0.0196
  -4.250   0.0017   0.01411   0.00661  -0.1140   0.9261   0.0215
  -4.000   0.0302   0.01365   0.00609  -0.1143   0.9186   0.0250
  -3.750   0.0630   0.01304   0.00536  -0.1153   0.9134   0.0289
  -3.500   0.0934   0.01259   0.00482  -0.1158   0.9068   0.0359
  -3.250   0.1249   0.01156   0.00420  -0.1171   0.9003   0.1341
  -3.000   0.1556   0.01070   0.00398  -0.1183   0.8940   0.3049
  -2.750   0.1845   0.01049   0.00396  -0.1185   0.8862   0.3827
  -2.500   0.2136   0.01041   0.00391  -0.1185   0.8789   0.4262
  -2.250   0.2424   0.01034   0.00379  -0.1184   0.8707   0.4431
  -2.000   0.2709   0.01028   0.00368  -0.1183   0.8623   0.4583
  -1.750   0.2999   0.01021   0.00357  -0.1182   0.8542   0.4730
  -1.500   0.3277   0.01016   0.00349  -0.1180   0.8444   0.4862
  -1.250   0.3561   0.01011   0.00341  -0.1179   0.8353   0.4989
  -1.000   0.3844   0.01007   0.00332  -0.1177   0.8256   0.5108
  -0.750   0.4122   0.01004   0.00327  -0.1174   0.8148   0.5228
  -0.500   0.4401   0.01001   0.00322  -0.1172   0.8040   0.5344
  -0.250   0.4680   0.00999   0.00318  -0.1170   0.7931   0.5459
   0.000   0.4958   0.00998   0.00315  -0.1167   0.7813   0.5577
   0.250   0.5234   0.00998   0.00315  -0.1164   0.7685   0.5698
   0.500   0.5509   0.00999   0.00315  -0.1161   0.7550   0.5826
   0.750   0.5783   0.01001   0.00316  -0.1158   0.7409   0.5957
   1.000   0.6054   0.01004   0.00318  -0.1154   0.7259   0.6094
   1.250   0.6324   0.01008   0.00322  -0.1150   0.7101   0.6235
   1.500   0.6593   0.01014   0.00327  -0.1146   0.6937   0.6384
   1.750   0.6860   0.01020   0.00335  -0.1141   0.6763   0.6542
   2.000   0.7124   0.01028   0.00343  -0.1136   0.6579   0.6711
   2.250   0.7385   0.01038   0.00352  -0.1131   0.6383   0.6896
   2.500   0.7642   0.01049   0.00365  -0.1125   0.6174   0.7103
   2.750   0.7893   0.01061   0.00376  -0.1117   0.5948   0.7335
   3.000   0.8137   0.01075   0.00389  -0.1108   0.5687   0.7616
   3.250   0.8367   0.01089   0.00402  -0.1096   0.5395   0.7989
   3.500   0.8561   0.01093   0.00413  -0.1076   0.5113   0.8739
   3.750   0.8813   0.01114   0.00427  -0.1070   0.4823   1.0000
   4.000   0.9066   0.01149   0.00449  -0.1065   0.4537   1.0000
   4.250   0.9315   0.01187   0.00475  -0.1060   0.4243   1.0000
   4.500   0.9562   0.01227   0.00505  -0.1055   0.3945   1.0000
   4.750   0.9806   0.01270   0.00536  -0.1050   0.3652   1.0000
   5.000   1.0045   0.01318   0.00571  -0.1044   0.3333   1.0000
   5.250   1.0277   0.01371   0.00609  -0.1038   0.2987   1.0000
   5.500   1.0507   0.01428   0.00654  -0.1031   0.2645   1.0000
   5.750   1.0735   0.01488   0.00701  -0.1025   0.2329   1.0000
   6.000   1.0956   0.01555   0.00753  -0.1017   0.2012   1.0000
   6.250   1.1175   0.01624   0.00809  -0.1010   0.1722   1.0000
   6.500   1.1395   0.01692   0.00869  -0.1002   0.1490   1.0000
   6.750   1.1613   0.01760   0.00930  -0.0994   0.1324   1.0000
   7.000   1.1830   0.01827   0.00994  -0.0986   0.1188   1.0000
   7.250   1.2047   0.01892   0.01060  -0.0978   0.1078   1.0000
   7.500   1.2262   0.01957   0.01128  -0.0969   0.0994   1.0000
   7.750   1.2463   0.02033   0.01206  -0.0959   0.0925   1.0000
   8.000   1.2675   0.02096   0.01278  -0.0949   0.0864   1.0000
   8.250   1.2867   0.02174   0.01358  -0.0938   0.0805   1.0000
   8.500   1.3065   0.02245   0.01438  -0.0927   0.0757   1.0000
   8.750   1.3257   0.02318   0.01517  -0.0916   0.0702   1.0000
   9.000   1.3432   0.02402   0.01608  -0.0903   0.0652   1.0000
   9.250   1.3621   0.02470   0.01687  -0.0891   0.0600   1.0000
   9.500   1.3773   0.02564   0.01781  -0.0876   0.0550   1.0000
   9.750   1.3950   0.02630   0.01863  -0.0862   0.0502   1.0000
  10.000   1.4085   0.02717   0.01953  -0.0844   0.0453   1.0000
  10.250   1.4223   0.02803   0.02052  -0.0826   0.0409   1.0000
  10.500   1.4346   0.02899   0.02152  -0.0808   0.0358   1.0000
  10.750   1.4457   0.03007   0.02272  -0.0789   0.0315   1.0000
  11.000   1.4549   0.03132   0.02401  -0.0769   0.0271   1.0000
  11.250   1.4633   0.03268   0.02549  -0.0750   0.0236   1.0000
  11.500   1.4694   0.03427   0.02715  -0.0730   0.0207   1.0000
  11.750   1.4736   0.03609   0.02908  -0.0710   0.0186   1.0000
  12.000   1.4781   0.03795   0.03109  -0.0693   0.0167   1.0000
  12.250   1.4800   0.04012   0.03336  -0.0677   0.0152   1.0000
  12.500   1.4796   0.04261   0.03598  -0.0663   0.0140   1.0000
  12.750   1.4806   0.04507   0.03862  -0.0651   0.0130   1.0000
  13.000   1.4800   0.04783   0.04155  -0.0643   0.0122   1.0000
  13.250   1.4774   0.05093   0.04482  -0.0637   0.0116   1.0000
  13.500   1.4726   0.05445   0.04850  -0.0635   0.0112   1.0000
  13.750   1.4652   0.05852   0.05273  -0.0638   0.0108   1.0000
  14.000   1.4548   0.06322   0.05763  -0.0645   0.0105   1.0000
  14.250   1.4454   0.06808   0.06266  -0.0657   0.0103   1.0000
  14.500   1.4362   0.07316   0.06795  -0.0672   0.0101   1.0000
  14.750   1.4258   0.07873   0.07372  -0.0693   0.0099   1.0000
  15.000   1.4142   0.08480   0.07999  -0.0718   0.0098   1.0000
  15.250   1.4014   0.09136   0.08675  -0.0748   0.0096   1.0000
  15.500   1.3879   0.09836   0.09395  -0.0782   0.0095   1.0000
  15.750   1.3735   0.10582   0.10159  -0.0821   0.0094   1.0000
  16.000   1.3585   0.11369   0.10965  -0.0864   0.0094   1.0000
  16.250   1.3435   0.12185   0.11799  -0.0911   0.0094   1.0000
  16.500   1.3278   0.13041   0.12672  -0.0961   0.0093   1.0000
  16.750   1.3124   0.13921   0.13568  -0.1014   0.0093   1.0000
  17.000   1.2971   0.14825   0.14487  -0.1070   0.0094   1.0000
  17.250   1.2820   0.15756   0.15434  -0.1129   0.0094   1.0000
  17.500   1.2669   0.16721   0.16412  -0.1190   0.0094   1.0000
  17.750   1.2514   0.17735   0.17439  -0.1255   0.0095   1.0000
  18.000   1.2348   0.18831   0.18544  -0.1326   0.0096   1.0000
  18.250   1.2143   0.20141   0.19864  -0.1408   0.0097   1.0000
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