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FX 66-17AII-182 AIRFOIL (fx6617a2-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 66-17AII-182 AIRFOIL (fx6617a2-il)
Reynolds number: 200,000
Max Cl/Cd: 65.03 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx6617a2-il-200000.txt
Download as CSV file: xf-fx6617a2-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1511   0.08964   0.08554  -0.0896   0.7380   0.0721
 -11.500  -0.1311   0.08818   0.08402  -0.0878   0.7289   0.0735
 -11.250  -0.2173   0.08371   0.07955  -0.1029   0.7583   0.0727
 -11.000  -0.1957   0.08360   0.07934  -0.1004   0.7462   0.0743
 -10.750  -0.1923   0.08053   0.07619  -0.1012   0.7382   0.0762
 -10.500  -0.2023   0.07511   0.07078  -0.1044   0.7314   0.0780
 -10.250  -0.2371   0.06701   0.06264  -0.1104   0.7267   0.0791
 -10.000  -0.2689   0.06174   0.05727  -0.1134   0.7218   0.0797
  -9.750  -0.3011   0.05773   0.05317  -0.1144   0.7158   0.0803
  -9.500  -0.4246   0.04311   0.03705  -0.1065   0.7147   0.0383
  -9.250  -0.4206   0.03911   0.03282  -0.1053   0.7097   0.0370
  -9.000  -0.4158   0.03597   0.02932  -0.1036   0.7048   0.0361
  -8.750  -0.4060   0.03322   0.02621  -0.1019   0.6993   0.0356
  -8.500  -0.3915   0.03094   0.02357  -0.1006   0.6944   0.0357
  -8.250  -0.3734   0.02906   0.02135  -0.0995   0.6902   0.0364
  -8.000  -0.3541   0.02785   0.01986  -0.0984   0.6851   0.0380
  -7.750  -0.3327   0.02594   0.01776  -0.0978   0.6808   0.0402
  -7.500  -0.3094   0.02481   0.01656  -0.0975   0.6771   0.0424
  -7.250  -0.2857   0.02384   0.01549  -0.0969   0.6735   0.0445
  -7.000  -0.2625   0.02316   0.01470  -0.0963   0.6694   0.0470
  -6.750  -0.2400   0.02199   0.01348  -0.0956   0.6656   0.0499
  -6.500  -0.2180   0.02131   0.01280  -0.0950   0.6621   0.0532
  -6.250  -0.1956   0.02072   0.01212  -0.0942   0.6590   0.0558
  -6.000  -0.1743   0.02017   0.01154  -0.0933   0.6552   0.0581
  -5.750  -0.1561   0.01936   0.01076  -0.0921   0.6518   0.0616
  -5.500  -0.1358   0.01879   0.01017  -0.0912   0.6487   0.0655
  -5.250  -0.1138   0.01834   0.00961  -0.0904   0.6460   0.0708
  -5.000  -0.0937   0.01771   0.00895  -0.0895   0.6436   0.0843
  -4.500  -0.0776   0.01481   0.00809  -0.0847   0.6376   0.4666
  -4.250  -0.0525   0.01517   0.00848  -0.0838   0.6343   0.5310
  -4.000  -0.0256   0.01557   0.00877  -0.0832   0.6315   0.5569
  -3.750   0.0017   0.01601   0.00908  -0.0828   0.6292   0.5759
  -3.500   0.0283   0.01658   0.00958  -0.0822   0.6268   0.5942
  -3.250   0.0539   0.01709   0.01012  -0.0813   0.6238   0.6090
  -3.000   0.0799   0.01751   0.01054  -0.0806   0.6207   0.6210
  -2.750   0.1060   0.01802   0.01103  -0.0796   0.6179   0.6356
  -2.500   0.1323   0.01839   0.01136  -0.0789   0.6154   0.6484
  -2.250   0.1596   0.01863   0.01151  -0.0786   0.6134   0.6563
  -2.000   0.1861   0.01869   0.01144  -0.0787   0.6113   0.6620
  -1.750   0.2109   0.01878   0.01157  -0.0782   0.6084   0.6658
  -1.500   0.2364   0.01890   0.01166  -0.0779   0.6054   0.6716
  -1.250   0.2622   0.01896   0.01164  -0.0778   0.6027   0.6783
  -1.000   0.2888   0.01905   0.01171  -0.0775   0.6004   0.6830
  -0.750   0.3162   0.01912   0.01169  -0.0776   0.5984   0.6880
  -0.500   0.3440   0.01922   0.01165  -0.0781   0.5966   0.6927
  -0.250   0.3678   0.01935   0.01183  -0.0776   0.5942   0.6956
   0.000   0.3918   0.01949   0.01201  -0.0773   0.5913   0.6990
   0.250   0.4174   0.01959   0.01209  -0.0772   0.5885   0.7028
   0.500   0.4440   0.01967   0.01210  -0.0774   0.5860   0.7068
   0.750   0.4711   0.01972   0.01211  -0.0776   0.5840   0.7098
   1.000   0.4987   0.01982   0.01218  -0.0777   0.5822   0.7128
   1.250   0.5265   0.02003   0.01233  -0.0780   0.5805   0.7165
   1.500   0.5470   0.02035   0.01274  -0.0772   0.5776   0.7203
   1.750   0.5700   0.02062   0.01303  -0.0769   0.5745   0.7240
   2.000   0.5946   0.02075   0.01320  -0.0766   0.5718   0.7271
   2.250   0.6207   0.02089   0.01336  -0.0766   0.5696   0.7304
   2.500   0.6480   0.02104   0.01348  -0.0768   0.5677   0.7338
   2.750   0.6767   0.02118   0.01356  -0.0773   0.5660   0.7373
   3.000   0.7008   0.02152   0.01393  -0.0772   0.5637   0.7406
   3.250   0.7169   0.02202   0.01460  -0.0757   0.5599   0.7436
   3.500   0.7387   0.02239   0.01503  -0.0752   0.5570   0.7467
   3.750   0.7642   0.02260   0.01527  -0.0752   0.5546   0.7502
   4.000   0.7920   0.02274   0.01538  -0.0755   0.5526   0.7542
   4.250   0.8204   0.02282   0.01548  -0.0758   0.5508   0.7576
   4.500   0.8495   0.02304   0.01571  -0.0763   0.5493   0.7611
   4.750   0.8542   0.02414   0.01703  -0.0734   0.5449   0.7650
   5.000   0.8702   0.02483   0.01782  -0.0722   0.5415   0.7691
   5.250   0.8937   0.02512   0.01817  -0.0719   0.5390   0.7732
   5.500   0.9219   0.02521   0.01832  -0.0722   0.5372   0.7777
   5.750   0.9515   0.02527   0.01841  -0.0727   0.5355   0.7829
   6.000   0.9819   0.02544   0.01859  -0.0735   0.5340   0.7877
   6.250   0.9614   0.02772   0.02119  -0.0674   0.5273   0.7929
   6.500   0.9754   0.02849   0.02207  -0.0659   0.5242   0.7991
   6.750   1.0025   0.02865   0.02231  -0.0661   0.5222   0.8053
   7.000   1.0344   0.02857   0.02229  -0.0669   0.5208   0.8129
   7.250   1.0678   0.02846   0.02226  -0.0679   0.5194   0.8213
   7.500   1.1022   0.02854   0.02240  -0.0692   0.5182   0.8310
   7.750   0.9413   0.03782   0.03208  -0.0486   0.4988   0.8528
   8.000   1.0007   0.03633   0.03076  -0.0523   0.4991   0.8771
   8.250   1.0869   0.03479   0.02949  -0.0614   0.4993   0.9536
   8.500   1.1789   0.03136   0.02606  -0.0687   0.5004   1.0000
   8.750   1.0980   0.03709   0.03185  -0.0575   0.4904   1.0000
   9.000   1.1013   0.03852   0.03332  -0.0557   0.4853   1.0000
   9.250   1.1613   0.03536   0.03021  -0.0577   0.4818   1.0000
   9.500   1.3317   0.02654   0.02131  -0.0730   0.4793   1.0000
   9.750   1.3833   0.02372   0.01837  -0.0751   0.4693   1.0000
  10.000   1.4133   0.02225   0.01683  -0.0746   0.4588   1.0000
  10.250   1.4099   0.02274   0.01748  -0.0699   0.4514   1.0000
  10.500   1.4346   0.02206   0.01679  -0.0689   0.4434   1.0000
  10.750   1.4237   0.02294   0.01785  -0.0634   0.4358   1.0000
  11.000   1.4294   0.02310   0.01805  -0.0603   0.4251   1.0000
  11.250   1.4327   0.02360   0.01858  -0.0574   0.4134   1.0000
  11.500   1.4271   0.02486   0.01992  -0.0541   0.4000   1.0000
  11.750   1.4209   0.02654   0.02167  -0.0514   0.3858   1.0000
  12.000   1.4111   0.02882   0.02397  -0.0491   0.3675   1.0000
  12.250   1.3976   0.03166   0.02676  -0.0470   0.3429   1.0000
  12.500   1.3809   0.03499   0.02996  -0.0451   0.3141   1.0000
  12.750   1.3566   0.03917   0.03396  -0.0432   0.2798   1.0000
  13.000   1.3319   0.04358   0.03818  -0.0415   0.2519   1.0000
  13.250   1.3050   0.04846   0.04288  -0.0402   0.2228   1.0000
  13.500   1.2802   0.05342   0.04766  -0.0392   0.1948   1.0000
  13.750   1.2567   0.05847   0.05254  -0.0385   0.1660   1.0000
  14.000   1.2311   0.06396   0.05780  -0.0380   0.1331   1.0000
  14.250   1.2077   0.06938   0.06297  -0.0377   0.1018   1.0000
  14.500   1.1890   0.07445   0.06783  -0.0377   0.0764   1.0000
  14.750   1.1732   0.07930   0.07251  -0.0376   0.0576   1.0000
  15.000   1.1630   0.08363   0.07678  -0.0377   0.0478   1.0000
  15.250   1.1544   0.08785   0.08099  -0.0380   0.0421   1.0000
  15.500   1.1526   0.09126   0.08446  -0.0382   0.0386   1.0000
  15.750   1.1471   0.09513   0.08833  -0.0385   0.0361   1.0000
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