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WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)
Reynolds number: 200,000
Max Cl/Cd: 62.93 at α=11°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx6617ai-il-200000.txt
Download as CSV file: xf-fx6617ai-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT N
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.3569   0.12031   0.11633  -0.0534   0.7419   0.0638
 -12.250  -0.3386   0.11794   0.11383  -0.0493   0.7297   0.0653
 -12.000  -0.3246   0.11629   0.11207  -0.0482   0.7203   0.0667
 -11.750  -0.3162   0.11359   0.10933  -0.0487   0.7123   0.0687
 -11.500  -0.3146   0.10974   0.10543  -0.0505   0.7065   0.0715
 -11.250  -0.3830   0.09317   0.08898  -0.0695   0.7092   0.0761
 -11.000  -0.3615   0.09134   0.08711  -0.0650   0.7021   0.0780
 -10.750  -0.3385   0.09211   0.08782  -0.0614   0.6943   0.0795
 -10.500  -0.2403   0.08006   0.07583  -0.0694   0.6766   0.0926
 -10.250  -0.2292   0.07811   0.07382  -0.0686   0.6729   0.0949
 -10.000  -0.2397   0.07242   0.06814  -0.0712   0.6706   0.0978
  -9.750  -0.2948   0.05988   0.05562  -0.0798   0.6712   0.0991
  -9.500  -0.5288   0.04408   0.03773  -0.0875   0.6844   0.0422
  -9.250  -0.5186   0.04036   0.03373  -0.0873   0.6797   0.0416
  -9.000  -0.5052   0.03785   0.03085  -0.0869   0.6754   0.0418
  -8.750  -0.4885   0.03555   0.02817  -0.0865   0.6717   0.0420
  -8.500  -0.4691   0.03311   0.02547  -0.0862   0.6673   0.0418
  -8.250  -0.4477   0.03103   0.02312  -0.0859   0.6630   0.0418
  -8.000  -0.4249   0.02968   0.02146  -0.0856   0.6590   0.0423
  -7.750  -0.4014   0.02829   0.01979  -0.0853   0.6554   0.0431
  -7.500  -0.3764   0.02632   0.01774  -0.0851   0.6513   0.0437
  -7.250  -0.3513   0.02487   0.01624  -0.0849   0.6475   0.0443
  -7.000  -0.3266   0.02378   0.01511  -0.0845   0.6442   0.0454
  -6.750  -0.3023   0.02293   0.01419  -0.0842   0.6413   0.0467
  -6.500  -0.2783   0.02216   0.01341  -0.0839   0.6382   0.0484
  -6.250  -0.2545   0.02145   0.01268  -0.0835   0.6349   0.0505
  -6.000  -0.2306   0.02080   0.01197  -0.0832   0.6316   0.0529
  -5.750  -0.2091   0.01988   0.01107  -0.0830   0.6286   0.0576
  -5.500  -0.1845   0.01938   0.01046  -0.0829   0.6258   0.0634
  -5.250  -0.1614   0.01862   0.00971  -0.0828   0.6231   0.0742
  -5.000  -0.1415   0.01720   0.00879  -0.0827   0.6202   0.1471
  -4.750  -0.1276   0.01528   0.00826  -0.0823   0.6175   0.4308
  -4.500  -0.1014   0.01538   0.00849  -0.0819   0.6148   0.4960
  -4.250  -0.0738   0.01568   0.00874  -0.0817   0.6123   0.5301
  -4.000  -0.0459   0.01611   0.00908  -0.0814   0.6101   0.5542
  -3.750  -0.0185   0.01667   0.00959  -0.0810   0.6077   0.5744
  -3.500   0.0086   0.01714   0.01007  -0.0805   0.6046   0.5903
  -3.250   0.0355   0.01766   0.01059  -0.0799   0.6017   0.6053
  -3.000   0.0625   0.01813   0.01104  -0.0793   0.5993   0.6186
  -2.750   0.0903   0.01836   0.01115  -0.0794   0.5971   0.6296
  -2.500   0.1181   0.01852   0.01127  -0.0792   0.5951   0.6343
  -2.250   0.1465   0.01870   0.01133  -0.0794   0.5933   0.6406
  -2.000   0.1737   0.01881   0.01141  -0.0797   0.5910   0.6472
  -1.750   0.2002   0.01904   0.01167  -0.0794   0.5882   0.6533
  -1.500   0.2280   0.01916   0.01171  -0.0797   0.5856   0.6618
  -1.250   0.2551   0.01927   0.01182  -0.0797   0.5832   0.6659
  -1.000   0.2831   0.01936   0.01185  -0.0799   0.5812   0.6708
  -0.750   0.3122   0.01943   0.01179  -0.0806   0.5795   0.6773
  -0.500   0.3399   0.01957   0.01190  -0.0807   0.5779   0.6807
  -0.250   0.3667   0.01980   0.01213  -0.0809   0.5759   0.6852
   0.000   0.3934   0.02000   0.01235  -0.0813   0.5733   0.6911
   0.250   0.4200   0.02015   0.01252  -0.0815   0.5707   0.6954
   0.500   0.4470   0.02030   0.01267  -0.0816   0.5684   0.6994
   0.750   0.4749   0.02046   0.01280  -0.0820   0.5664   0.7046
   1.000   0.5032   0.02060   0.01289  -0.0825   0.5647   0.7099
   1.250   0.5307   0.02077   0.01305  -0.0826   0.5632   0.7140
   1.500   0.5589   0.02102   0.01326  -0.0830   0.5617   0.7187
   1.750   0.5843   0.02142   0.01371  -0.0833   0.5593   0.7243
   2.000   0.6079   0.02178   0.01419  -0.0831   0.5564   0.7282
   2.250   0.6332   0.02210   0.01457  -0.0832   0.5539   0.7331
   2.500   0.6603   0.02240   0.01487  -0.0836   0.5519   0.7386
   2.750   0.6874   0.02261   0.01510  -0.0838   0.5502   0.7428
   3.000   0.7145   0.02282   0.01534  -0.0840   0.5486   0.7474
   3.250   0.7430   0.02303   0.01552  -0.0845   0.5471   0.7530
   3.500   0.7715   0.02331   0.01577  -0.0849   0.5457   0.7578
   3.750   0.7879   0.02422   0.01693  -0.0841   0.5420   0.7623
   4.000   0.8094   0.02496   0.01777  -0.0840   0.5392   0.7677
   4.250   0.8334   0.02546   0.01834  -0.0841   0.5368   0.7729
   4.500   0.8593   0.02571   0.01866  -0.0841   0.5349   0.7780
   4.750   0.8881   0.02585   0.01880  -0.0846   0.5333   0.7838
   5.000   0.9163   0.02601   0.01898  -0.0849   0.5319   0.7891
   5.250   0.9438   0.02630   0.01931  -0.0852   0.5306   0.7949
   5.500   0.9471   0.02845   0.02175  -0.0835   0.5254   0.8014
   5.750   0.9628   0.02942   0.02288  -0.0827   0.5217   0.8071
   6.000   0.9866   0.02989   0.02343  -0.0827   0.5197   0.8142
   6.250   1.0138   0.03006   0.02366  -0.0828   0.5181   0.8210
   6.500   1.0438   0.03001   0.02366  -0.0832   0.5169   0.8288
   6.750   1.0736   0.03001   0.02370  -0.0836   0.5157   0.8369
   7.250   0.9786   0.04179   0.03612  -0.0735   0.4948   0.8599
   7.500   1.0254   0.04007   0.03447  -0.0742   0.4957   0.8739
   7.750   1.0764   0.03823   0.03273  -0.0757   0.4968   0.8937
   8.000   1.1319   0.03622   0.03085  -0.0778   0.4980   0.9439
   8.250   1.1923   0.03436   0.02896  -0.0813   0.4993   1.0002
   8.500   1.0900   0.04438   0.03918  -0.0733   0.4835   1.0002
   8.750   1.1372   0.04293   0.03778  -0.0746   0.4838   1.0002
   9.000   1.2211   0.03861   0.03348  -0.0786   0.4855   1.0002
   9.500   1.3334   0.03178   0.02664  -0.0820   0.4746   1.0002
   9.750   1.4113   0.02744   0.02215  -0.0865   0.4712   1.0002
  10.000   1.4203   0.02803   0.02291  -0.0844   0.4648   1.0002
  10.250   1.4666   0.02556   0.02038  -0.0857   0.4571   1.0002
  10.500   1.4807   0.02521   0.02015  -0.0837   0.4477   1.0002
  10.750   1.5010   0.02410   0.01907  -0.0820   0.4354   1.0002
  11.000   1.5052   0.02392   0.01897  -0.0785   0.4208   1.0002
  11.250   1.5023   0.02459   0.01971  -0.0750   0.4019   1.0002
  11.500   1.4929   0.02625   0.02137  -0.0720   0.3747   1.0002
  11.750   1.4731   0.02941   0.02433  -0.0694   0.3335   1.0002
  12.000   1.4439   0.03416   0.02886  -0.0674   0.2965   1.0002
  12.250   1.4125   0.03954   0.03408  -0.0658   0.2659   1.0002
  12.500   1.3807   0.04508   0.03946  -0.0644   0.2370   1.0002
  12.750   1.3492   0.05066   0.04489  -0.0630   0.2074   1.0002
  13.000   1.3174   0.05658   0.05063  -0.0620   0.1768   1.0002
  13.250   1.2870   0.06261   0.05645  -0.0612   0.1452   1.0002
  13.500   1.2586   0.06864   0.06225  -0.0607   0.1123   1.0002
  13.750   1.2348   0.07432   0.06772  -0.0603   0.0868   1.0002
  14.000   1.2187   0.07924   0.07252  -0.0601   0.0721   1.0002
  14.250   1.2078   0.08365   0.07689  -0.0600   0.0639   1.0002
  14.500   1.2003   0.08769   0.08092  -0.0600   0.0582   1.0002
  14.750   1.1945   0.09154   0.08479  -0.0600   0.0539   1.0002
  15.000   1.1936   0.09477   0.08807  -0.0600   0.0499   1.0002
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