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FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il)
Reynolds number: 100,000
Max Cl/Cd: 29.16 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx6617a2-il-100000-n5.txt
Download as CSV file: xf-fx6617a2-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 66-17AII-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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.2701   0.09676   0.09176  -0.0802   0.8432   0.0285
 -12.000  -0.3759   0.07056   0.06533  -0.0963   0.8545   0.0252
 -11.750  -0.3921   0.06404   0.05846  -0.1022   0.8266   0.0251
 -11.500  -0.4066   0.05929   0.05339  -0.1054   0.8042   0.0250
 -11.250  -0.4252   0.05507   0.04881  -0.1072   0.7862   0.0251
 -10.750  -0.4460   0.04904   0.04229  -0.1078   0.7577   0.0257
 -10.500  -0.4501   0.04685   0.03989  -0.1071   0.7463   0.0260
 -10.250  -0.4494   0.04528   0.03818  -0.1060   0.7365   0.0267
 -10.000  -0.4491   0.04374   0.03643  -0.1044   0.7276   0.0274
  -9.750  -0.4473   0.04170   0.03409  -0.1029   0.7203   0.0282
  -9.500  -0.4417   0.03958   0.03164  -0.1017   0.7131   0.0289
  -9.250  -0.4320   0.03740   0.02906  -0.1005   0.7073   0.0296
  -9.000  -0.4191   0.03535   0.02663  -0.0993   0.7007   0.0306
  -8.750  -0.4022   0.03360   0.02459  -0.0985   0.6948   0.0317
  -8.500  -0.3837   0.03247   0.02339  -0.0980   0.6894   0.0334
  -8.250  -0.3646   0.03135   0.02213  -0.0974   0.6836   0.0354
  -8.000  -0.3431   0.03015   0.02067  -0.0967   0.6787   0.0373
  -7.750  -0.3213   0.02902   0.01935  -0.0961   0.6747   0.0396
  -7.500  -0.3008   0.02804   0.01840  -0.0955   0.6698   0.0417
  -7.250  -0.2794   0.02714   0.01743  -0.0947   0.6654   0.0437
  -7.000  -0.2582   0.02640   0.01654  -0.0939   0.6616   0.0463
  -6.750  -0.2385   0.02563   0.01567  -0.0929   0.6577   0.0489
  -6.500  -0.2208   0.02488   0.01493  -0.0918   0.6534   0.0512
  -6.250  -0.2022   0.02425   0.01423  -0.0906   0.6494   0.0540
  -6.000  -0.1829   0.02367   0.01350  -0.0896   0.6461   0.0575
  -5.750  -0.1641   0.02304   0.01281  -0.0886   0.6433   0.0629
  -5.500  -0.1452   0.02249   0.01226  -0.0876   0.6396   0.0725
  -5.250  -0.1272   0.02180   0.01168  -0.0865   0.6362   0.0916
  -5.000  -0.1102   0.02097   0.01107  -0.0854   0.6330   0.1421
  -4.750  -0.0959   0.01985   0.01041  -0.0842   0.6302   0.2503
  -4.500  -0.0815   0.01898   0.01018  -0.0826   0.6277   0.3841
  -4.250  -0.0614   0.01934   0.01102  -0.0806   0.6240   0.4962
  -4.000  -0.0377   0.01988   0.01147  -0.0795   0.6206   0.5502
  -3.750  -0.0133   0.02055   0.01203  -0.0783   0.6178   0.5804
  -3.500   0.0122   0.02107   0.01245  -0.0772   0.6153   0.5992
  -3.250   0.0380   0.02136   0.01255  -0.0765   0.6130   0.6134
  -3.000   0.0638   0.02159   0.01271  -0.0758   0.6102   0.6202
  -2.750   0.0877   0.02163   0.01260  -0.0755   0.6068   0.6287
  -2.500   0.1131   0.02176   0.01267  -0.0750   0.6038   0.6342
  -2.250   0.1384   0.02185   0.01262  -0.0746   0.6011   0.6427
  -2.000   0.1645   0.02193   0.01260  -0.0743   0.5989   0.6490
  -1.750   0.1914   0.02197   0.01250  -0.0742   0.5970   0.6540
  -1.500   0.2160   0.02202   0.01243  -0.0742   0.5942   0.6597
  -1.250   0.2397   0.02212   0.01251  -0.0737   0.5910   0.6637
  -1.000   0.2645   0.02221   0.01256  -0.0733   0.5881   0.6679
  -0.750   0.2901   0.02228   0.01252  -0.0733   0.5856   0.6729
  -0.500   0.3165   0.02232   0.01246  -0.0734   0.5835   0.6775
  -0.250   0.3435   0.02237   0.01244  -0.0734   0.5816   0.6807
   0.000   0.3688   0.02249   0.01250  -0.0732   0.5794   0.6842
   0.250   0.3907   0.02271   0.01274  -0.0727   0.5760   0.6881
   0.500   0.4146   0.02288   0.01286  -0.0726   0.5730   0.6921
   0.750   0.4394   0.02302   0.01299  -0.0723   0.5706   0.6949
   1.000   0.4651   0.02315   0.01310  -0.0722   0.5685   0.6980
   1.250   0.4920   0.02326   0.01315  -0.0724   0.5667   0.7014
   1.500   0.5200   0.02335   0.01317  -0.0727   0.5650   0.7051
   1.750   0.5389   0.02377   0.01365  -0.0718   0.5616   0.7088
   2.000   0.5592   0.02412   0.01407  -0.0710   0.5583   0.7117
   2.250   0.5824   0.02440   0.01438  -0.0707   0.5556   0.7148
   2.500   0.6074   0.02463   0.01462  -0.0706   0.5535   0.7184
   2.750   0.6341   0.02482   0.01478  -0.0708   0.5516   0.7225
   3.000   0.6619   0.02495   0.01489  -0.0711   0.5500   0.7258
   3.250   0.6807   0.02541   0.01545  -0.0701   0.5470   0.7292
   3.500   0.6938   0.02612   0.01628  -0.0685   0.5430   0.7328
   3.750   0.7135   0.02660   0.01681  -0.0677   0.5401   0.7370
   4.000   0.7370   0.02691   0.01717  -0.0675   0.5378   0.7410
   4.250   0.7638   0.02709   0.01738  -0.0676   0.5359   0.7449
   4.500   0.7929   0.02723   0.01752  -0.0681   0.5343   0.7492
   4.750   0.7989   0.02836   0.01881  -0.0657   0.5299   0.7539
   5.000   0.8063   0.02942   0.02001  -0.0635   0.5256   0.7581
   5.250   0.8269   0.02988   0.02054  -0.0630   0.5228   0.7630
   5.500   0.8533   0.03011   0.02082  -0.0631   0.5208   0.7688
   5.750   0.8821   0.03025   0.02103  -0.0635   0.5193   0.7743
   6.250   0.8554   0.03428   0.02537  -0.0548   0.5076   0.7881
   6.500   0.8808   0.03451   0.02571  -0.0548   0.5056   0.7953
   6.750   0.9111   0.03458   0.02588  -0.0554   0.5042   0.8040
   7.000   0.9446   0.03453   0.02594  -0.0564   0.5031   0.8145
   7.500   0.8912   0.04164   0.03345  -0.0488   0.4870   0.8577
   8.000   0.8840   0.04772   0.03978  -0.0483   0.4725   1.0000
   8.500   0.8813   0.05316   0.04529  -0.0470   0.4585   1.0000
   9.000   0.8802   0.05848   0.05070  -0.0460   0.4447   1.0000
   9.250   0.9076   0.05849   0.05079  -0.0460   0.4435   1.0000
   9.750   0.9095   0.06353   0.05594  -0.0450   0.4297   1.0000
  10.250   0.9171   0.06800   0.06057  -0.0443   0.4163   1.0000
  10.500   0.9446   0.06779   0.06045  -0.0441   0.4146   1.0000
  11.000   0.9552   0.07190   0.06472  -0.0435   0.4010   1.0000
  11.500   0.9698   0.07552   0.06855  -0.0429   0.3875   1.0000
  12.000   0.9880   0.07867   0.07191  -0.0423   0.3738   1.0000
  12.500   1.0147   0.08043   0.07390  -0.0416   0.3595   1.0000
  12.750   1.0304   0.08048   0.07408  -0.0410   0.3491   1.0000
  13.000   1.0592   0.07841   0.07210  -0.0400   0.3376   1.0000
  13.250   1.0668   0.07969   0.07346  -0.0397   0.3214   1.0000
  13.500   1.0762   0.08109   0.07495  -0.0396   0.3069   1.0000
  13.750   1.0826   0.08303   0.07697  -0.0395   0.2901   1.0000
  14.000   1.1045   0.08263   0.07658  -0.0390   0.2687   1.0000
  14.250   1.1279   0.08179   0.07550  -0.0381   0.2309   1.0000
  14.500   1.1328   0.08358   0.07696  -0.0377   0.1930   1.0000
  14.750   1.1263   0.08724   0.08038  -0.0378   0.1619   1.0000
  15.000   1.1171   0.09146   0.08440  -0.0382   0.1346   1.0000
  15.250   1.1078   0.09583   0.08861  -0.0387   0.1107   1.0000
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