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FX 66-182 AIRFOIL (fx66182-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-182 AIRFOIL (fx66182-il)
Reynolds number: 100,000
Max Cl/Cd: 30.19 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx66182-il-100000-n5.txt
Download as CSV file: xf-fx66182-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-182 AIRFOIL                               
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3159   0.09744   0.09273  -0.0733   0.8915   0.0273
 -12.250  -0.3210   0.08691   0.08204  -0.0826   0.8672   0.0270
 -12.000  -0.3364   0.07715   0.07205  -0.0914   0.8422   0.0266
 -11.500  -0.3805   0.06317   0.05751  -0.1023   0.8000   0.0262
 -11.250  -0.3999   0.05836   0.05242  -0.1049   0.7833   0.0262
 -11.000  -0.4166   0.05432   0.04808  -0.1063   0.7691   0.0261
 -10.500  -0.4441   0.04775   0.04090  -0.1065   0.7459   0.0263
 -10.250  -0.4541   0.04521   0.03803  -0.1050   0.7366   0.0264
 -10.000  -0.4600   0.04281   0.03525  -0.1031   0.7284   0.0268
  -9.750  -0.4590   0.04040   0.03240  -0.1015   0.7210   0.0272
  -9.500  -0.4488   0.03840   0.03019  -0.1007   0.7137   0.0279
  -9.250  -0.4345   0.03717   0.02886  -0.1001   0.7071   0.0293
  -9.000  -0.4196   0.03572   0.02720  -0.0994   0.7003   0.0305
  -8.750  -0.4034   0.03412   0.02526  -0.0985   0.6948   0.0322
  -8.500  -0.3844   0.03252   0.02331  -0.0977   0.6891   0.0334
  -8.250  -0.3642   0.03111   0.02182  -0.0973   0.6838   0.0352
  -8.000  -0.3440   0.03014   0.02075  -0.0967   0.6793   0.0374
  -7.750  -0.3221   0.02909   0.01952  -0.0962   0.6747   0.0395
  -7.500  -0.3000   0.02822   0.01843  -0.0955   0.6697   0.0418
  -7.250  -0.2793   0.02714   0.01738  -0.0948   0.6654   0.0441
  -7.000  -0.2584   0.02631   0.01648  -0.0940   0.6618   0.0461
  -6.750  -0.2388   0.02558   0.01570  -0.0931   0.6572   0.0482
  -6.500  -0.2187   0.02498   0.01497  -0.0921   0.6531   0.0514
  -6.250  -0.2008   0.02424   0.01421  -0.0911   0.6497   0.0547
  -6.000  -0.1813   0.02364   0.01351  -0.0901   0.6468   0.0584
  -5.750  -0.1618   0.02309   0.01288  -0.0891   0.6432   0.0633
  -5.500  -0.1432   0.02246   0.01226  -0.0882   0.6394   0.0719
  -5.250  -0.1243   0.02178   0.01164  -0.0873   0.6360   0.0921
  -5.000  -0.1071   0.02087   0.01100  -0.0864   0.6330   0.1493
  -4.500  -0.0774   0.01897   0.01040  -0.0839   0.6270   0.4088
  -4.250  -0.0547   0.01935   0.01104  -0.0824   0.6237   0.5031
  -4.000  -0.0299   0.01998   0.01159  -0.0814   0.6208   0.5529
  -3.750  -0.0047   0.02065   0.01213  -0.0802   0.6181   0.5828
  -3.500   0.0212   0.02121   0.01257  -0.0791   0.6157   0.6015
  -3.250   0.0460   0.02156   0.01282  -0.0782   0.6128   0.6157
  -3.000   0.0702   0.02178   0.01293  -0.0775   0.6094   0.6282
  -2.750   0.0954   0.02197   0.01307  -0.0768   0.6064   0.6348
  -2.500   0.1215   0.02197   0.01288  -0.0768   0.6039   0.6430
  -2.250   0.1480   0.02202   0.01281  -0.0766   0.6016   0.6474
  -2.000   0.1753   0.02203   0.01267  -0.0766   0.5996   0.6521
  -1.750   0.2003   0.02205   0.01259  -0.0767   0.5966   0.6574
  -1.500   0.2250   0.02210   0.01259  -0.0765   0.5934   0.6613
  -1.250   0.2504   0.02217   0.01259  -0.0763   0.5905   0.6648
  -1.000   0.2768   0.02221   0.01254  -0.0763   0.5882   0.6690
  -0.750   0.3042   0.02223   0.01242  -0.0767   0.5861   0.6738
  -0.500   0.3318   0.02226   0.01235  -0.0769   0.5842   0.6772
  -0.250   0.3561   0.02240   0.01248  -0.0766   0.5814   0.6804
   0.000   0.3795   0.02259   0.01267  -0.0763   0.5782   0.6842
   0.250   0.4048   0.02273   0.01277  -0.0764   0.5754   0.6882
   0.500   0.4309   0.02286   0.01284  -0.0765   0.5731   0.6917
   0.750   0.4572   0.02297   0.01292  -0.0765   0.5711   0.6946
   1.000   0.4847   0.02305   0.01295  -0.0767   0.5692   0.6979
   1.250   0.5117   0.02319   0.01303  -0.0769   0.5672   0.7015
   1.500   0.5319   0.02359   0.01349  -0.0764   0.5635   0.7053
   1.750   0.5544   0.02388   0.01384  -0.0760   0.5606   0.7084
   2.000   0.5784   0.02413   0.01412  -0.0757   0.5582   0.7116
   2.250   0.6043   0.02433   0.01431  -0.0758   0.5561   0.7149
   2.500   0.6321   0.02449   0.01444  -0.0762   0.5543   0.7187
   2.750   0.6610   0.02460   0.01451  -0.0767   0.5526   0.7225
   3.000   0.6767   0.02521   0.01526  -0.0754   0.5489   0.7258
   3.250   0.6947   0.02577   0.01592  -0.0744   0.5455   0.7294
   3.500   0.7168   0.02618   0.01638  -0.0741   0.5429   0.7332
   4.000   0.7687   0.02661   0.01685  -0.0742   0.5388   0.7410
   4.250   0.7973   0.02673   0.01699  -0.0745   0.5372   0.7452
   4.500   0.8035   0.02789   0.01833  -0.0723   0.5326   0.7499
   4.750   0.8168   0.02873   0.01928  -0.0709   0.5287   0.7542
   5.000   0.8384   0.02913   0.01977  -0.0704   0.5260   0.7584
   5.250   0.8644   0.02936   0.02005  -0.0704   0.5241   0.7636
   5.500   0.8924   0.02956   0.02030  -0.0708   0.5225   0.7694
   6.000   0.8842   0.03285   0.02392  -0.0642   0.5120   0.7820
   6.250   0.9057   0.03324   0.02442  -0.0637   0.5097   0.7885
   6.500   0.9327   0.03339   0.02466  -0.0638   0.5080   0.7961
   6.750   0.9614   0.03351   0.02488  -0.0641   0.5068   0.8049
   8.250   0.8579   0.05345   0.04562  -0.0496   0.4594   1.0000
   8.750   0.8748   0.05711   0.04937  -0.0490   0.4488   1.0000
   9.000   0.8563   0.06154   0.05383  -0.0483   0.4386   1.0000
   9.250   0.8776   0.06214   0.05450  -0.0482   0.4357   1.0000
   9.500   0.9033   0.06230   0.05474  -0.0482   0.4338   1.0000
   9.750   0.9312   0.06220   0.05472  -0.0481   0.4325   1.0000
  10.250   0.9372   0.06678   0.05945  -0.0474   0.4188   1.0000
  11.250   0.9616   0.07477   0.06780  -0.0463   0.3921   1.0000
  11.500   0.9899   0.07423   0.06739  -0.0459   0.3900   1.0000
  12.000   1.0092   0.07715   0.07054  -0.0453   0.3761   1.0000
  12.250   1.0043   0.08032   0.07379  -0.0452   0.3651   1.0000
  12.500   1.0421   0.07773   0.07135  -0.0444   0.3614   1.0000
  13.000   1.0598   0.07965   0.07346  -0.0435   0.3361   1.0000
  13.250   1.0736   0.08006   0.07397  -0.0431   0.3211   1.0000
  13.500   1.0868   0.08079   0.07477  -0.0428   0.3042   1.0000
  13.750   1.0961   0.08230   0.07634  -0.0427   0.2859   1.0000
  14.000   1.1074   0.08360   0.07767  -0.0425   0.2663   1.0000
  14.250   1.1370   0.08182   0.07565  -0.0414   0.2301   1.0000
  14.500   1.1400   0.08396   0.07747  -0.0411   0.1917   1.0000
  14.750   1.1320   0.08788   0.08111  -0.0414   0.1583   1.0000
  15.000   1.1225   0.09225   0.08529  -0.0420   0.1310   1.0000
  15.250   1.1135   0.09672   0.08959  -0.0427   0.1070   1.0000
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