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FX 61-168 AIRFOIL (fx61168-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 61-168 AIRFOIL (fx61168-il)
Reynolds number: 50,000
Max Cl/Cd: 15.36 at α=12°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx61168-il-50000-n5.txt
Download as CSV file: xf-fx61168-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 61-168 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3741   0.11123   0.10422  -0.0574   1.0000   0.0424
 -11.500  -0.3741   0.10701   0.10006  -0.0583   1.0000   0.0421
 -11.250  -0.3780   0.10208   0.09520  -0.0600   1.0000   0.0417
 -11.000  -0.3850   0.09698   0.09016  -0.0619   1.0000   0.0413
 -10.750  -0.3968   0.09155   0.08479  -0.0642   1.0000   0.0408
 -10.500  -0.4130   0.08623   0.07951  -0.0664   1.0000   0.0404
 -10.250  -0.4323   0.08144   0.07476  -0.0679   1.0000   0.0400
 -10.000  -0.4546   0.07722   0.07056  -0.0685   1.0000   0.0396
  -9.750  -0.4781   0.07385   0.06721  -0.0679   1.0000   0.0393
  -9.500  -0.5045   0.07126   0.06467  -0.0659   1.0000   0.0391
  -9.250  -0.5332   0.06980   0.06328  -0.0622   1.0000   0.0388
  -9.000  -0.5581   0.06803   0.06152  -0.0598   0.9968   0.0386
  -8.750  -0.5516   0.06280   0.05591  -0.0651   0.9787   0.0385
  -8.500  -0.5410   0.05820   0.05088  -0.0687   0.9621   0.0385
  -8.250  -0.5274   0.05427   0.04651  -0.0710   0.9467   0.0388
  -8.000  -0.5083   0.05061   0.04234  -0.0732   0.9340   0.0401
  -7.750  -0.4876   0.04753   0.03869  -0.0746   0.9212   0.0416
  -7.500  -0.4632   0.04463   0.03536  -0.0756   0.9100   0.0432
  -7.250  -0.4298   0.04190   0.03240  -0.0773   0.9031   0.0448
  -7.000  -0.3981   0.03983   0.03012  -0.0780   0.8941   0.0465
  -6.750  -0.3564   0.03795   0.02798  -0.0796   0.8893   0.0507
  -6.500  -0.3206   0.03670   0.02652  -0.0794   0.8807   0.0549
  -6.250  -0.2777   0.03543   0.02523  -0.0803   0.8760   0.0604
  -6.000  -0.2483   0.03445   0.02407  -0.0801   0.8670   0.0679
  -5.750  -0.2198   0.03312   0.02271  -0.0810   0.8599   0.0773
  -5.500  -0.2044   0.03199   0.02157  -0.0802   0.8491   0.0889
  -5.250  -0.1877   0.03051   0.02018  -0.0801   0.8403   0.1107
  -5.000  -0.1805   0.02834   0.01862  -0.0796   0.8308   0.1750
  -4.750  -0.1794   0.02844   0.02083  -0.0725   0.8219   0.4932
  -4.500  -0.1533   0.03064   0.02273  -0.0694   0.8151   0.5910
  -4.250  -0.1243   0.03473   0.02663  -0.0619   0.8085   0.6464
  -4.000  -0.1014   0.03521   0.02681  -0.0603   0.8016   0.6674
  -3.750  -0.0677   0.03511   0.02636  -0.0607   0.7964   0.6744
  -3.500  -0.0550   0.03493   0.02598  -0.0592   0.7881   0.6846
  -3.250  -0.0237   0.03466   0.02542  -0.0599   0.7832   0.6928
  -2.750   0.0128   0.03435   0.02471  -0.0580   0.7696   0.7099
  -2.500   0.0343   0.03425   0.02443  -0.0573   0.7638   0.7167
  -2.250   0.0488   0.03417   0.02421  -0.0560   0.7568   0.7254
  -2.000   0.0796   0.03395   0.02378  -0.0565   0.7525   0.7319
  -1.750   0.0871   0.03405   0.02379  -0.0541   0.7448   0.7406
  -1.250   0.1373   0.03379   0.02323  -0.0539   0.7349   0.7539
  -1.000   0.1440   0.03398   0.02337  -0.0512   0.7272   0.7605
  -0.750   0.1719   0.03383   0.02308  -0.0515   0.7228   0.7661
  -0.500   0.1836   0.03396   0.02313  -0.0501   0.7161   0.7732
  -0.250   0.2013   0.03405   0.02316  -0.0487   0.7102   0.7780
   0.000   0.2320   0.03388   0.02285  -0.0497   0.7063   0.7837
   0.250   0.2361   0.03429   0.02325  -0.0470   0.6983   0.7895
   0.500   0.2597   0.03431   0.02320  -0.0467   0.6933   0.7943
   0.750   0.2945   0.03411   0.02288  -0.0483   0.6899   0.7993
   1.000   0.2919   0.03477   0.02358  -0.0447   0.6806   0.8048
   1.250   0.3211   0.03469   0.02342  -0.0451   0.6764   0.8092
   1.500   0.3288   0.03524   0.02397  -0.0432   0.6686   0.8147
   1.750   0.3520   0.03540   0.02409  -0.0432   0.6631   0.8193
   2.000   0.3857   0.03524   0.02389  -0.0442   0.6596   0.8232
   2.250   0.3830   0.03621   0.02490  -0.0411   0.6499   0.8288
   2.500   0.4157   0.03621   0.02487  -0.0424   0.6458   0.8331
   2.750   0.4171   0.03705   0.02576  -0.0394   0.6373   0.8379
   3.000   0.4424   0.03727   0.02597  -0.0397   0.6319   0.8424
   3.250   0.4818   0.03715   0.02583  -0.0418   0.6288   0.8466
   3.500   0.4711   0.03845   0.02722  -0.0377   0.6179   0.8517
   3.750   0.5070   0.03832   0.02710  -0.0390   0.6143   0.8558
   4.000   0.5044   0.03979   0.02863  -0.0367   0.6036   0.8613
   4.250   0.5365   0.03965   0.02851  -0.0373   0.5995   0.8653
   4.500   0.5346   0.04120   0.03016  -0.0351   0.5891   0.8708
   4.750   0.5670   0.04122   0.03021  -0.0360   0.5846   0.8752
   5.250   0.5951   0.04295   0.03209  -0.0346   0.5695   0.8852
   5.750   0.6253   0.04485   0.03417  -0.0338   0.5542   0.8956
   6.250   0.6567   0.04680   0.03630  -0.0334   0.5387   0.9071
   6.750   0.6892   0.04866   0.03839  -0.0330   0.5231   0.9197
   7.250   0.7220   0.05054   0.04051  -0.0327   0.5076   0.9348
   7.500   0.7204   0.05311   0.04320  -0.0325   0.4954   0.9446
   7.750   0.7590   0.05245   0.04271  -0.0334   0.4920   0.9553
   8.250   0.7670   0.05736   0.04786  -0.0348   0.4678   1.0000
   8.500   0.8069   0.05674   0.04741  -0.0359   0.4632   1.0000
   9.000   0.8558   0.05825   0.04920  -0.0378   0.4474   1.0000
   9.250   0.8589   0.06116   0.05223  -0.0387   0.4346   1.0000
   9.500   0.8654   0.06380   0.05500  -0.0396   0.4228   1.0000
   9.750   0.9080   0.06238   0.05379  -0.0401   0.4185   1.0000
  10.000   0.9125   0.06514   0.05667  -0.0409   0.4056   1.0000
  10.500   0.9625   0.06577   0.05766  -0.0418   0.3889   1.0000
  10.750   0.9653   0.06877   0.06079  -0.0425   0.3760   1.0000
  11.250   1.0174   0.06877   0.06114  -0.0428   0.3591   1.0000
  11.500   1.0196   0.07174   0.06424  -0.0434   0.3460   1.0000
  12.000   1.0791   0.07027   0.06316  -0.0429   0.3282   1.0000
  12.500   1.0793   0.07671   0.06987  -0.0441   0.3018   1.0000
  13.000   1.0975   0.08049   0.07391  -0.0446   0.2766   1.0000
  13.250   1.1149   0.08103   0.07458  -0.0444   0.2640   1.0000
  13.500   1.1306   0.08178   0.07546  -0.0443   0.2507   1.0000
  13.750   1.1453   0.08273   0.07649  -0.0442   0.2374   1.0000
  14.000   1.1534   0.08459   0.07840  -0.0444   0.2231   1.0000
  14.250   1.1565   0.08725   0.08110  -0.0449   0.2086   1.0000
  14.500   1.1585   0.09017   0.08405  -0.0457   0.1944   1.0000
  14.750   1.1613   0.09302   0.08690  -0.0464   0.1808   1.0000
  15.000   1.1647   0.09583   0.08969  -0.0471   0.1678   1.0000
  15.250   1.1617   0.09992   0.09387  -0.0485   0.1561   1.0000
  15.500   1.1565   0.10456   0.09861  -0.0502   0.1452   1.0000
  15.750   1.1548   0.10859   0.10268  -0.0518   0.1348   1.0000
  16.000   1.1573   0.11181   0.10590  -0.0529   0.1248   1.0000
  16.250   1.1558   0.11596   0.11012  -0.0547   0.1159   1.0000
  16.500   1.1500   0.12113   0.11541  -0.0570   0.1083   1.0000
  16.750   1.1569   0.12354   0.11771  -0.0580   0.1003   1.0000
  17.000   1.1445   0.13046   0.12492  -0.0616   0.0951   1.0000
  17.250   1.1568   0.13174   0.12605  -0.0620   0.0880   1.0000
  17.500   1.1395   0.14003   0.13465  -0.0666   0.0846   1.0000
  17.750   1.1245   0.14800   0.14283  -0.0713   0.0810   1.0000
  18.000   1.1437   0.14765   0.14234  -0.0708   0.0752   1.0000
  18.250   1.1172   0.15889   0.15385  -0.0777   0.0739   1.0000
  18.500   1.0761   0.17526   0.17033  -0.0879   0.0732   1.0000
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