Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)
Reynolds number: 500,000
Max Cl/Cd: 105.55 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx6617ai-il-500000-n5.txt
Download as CSV file: xf-fx6617ai-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -16.250  -0.6639   0.10493   0.10158  -0.0411   0.7695   0.0102
 -16.000  -0.7037   0.09244   0.08887  -0.0483   0.7654   0.0102
 -15.750  -0.7302   0.08323   0.07941  -0.0538   0.7503   0.0102
 -15.500  -0.7501   0.07579   0.07173  -0.0584   0.7330   0.0102
 -15.250  -0.7654   0.06950   0.06520  -0.0622   0.7160   0.0103
 -15.000  -0.7790   0.06389   0.05936  -0.0655   0.7009   0.0103
 -14.750  -0.7909   0.05891   0.05418  -0.0682   0.6876   0.0104
 -14.500  -0.7993   0.05477   0.04985  -0.0702   0.6756   0.0105
 -14.250  -0.8038   0.05123   0.04615  -0.0719   0.6649   0.0106
 -14.000  -0.8052   0.04820   0.04298  -0.0732   0.6551   0.0107
 -13.750  -0.8039   0.04553   0.04017  -0.0744   0.6461   0.0108
 -13.500  -0.8005   0.04317   0.03769  -0.0754   0.6382   0.0109
 -13.250  -0.7955   0.04100   0.03541  -0.0762   0.6309   0.0111
 -13.000  -0.7893   0.03901   0.03330  -0.0770   0.6245   0.0112
 -12.750  -0.7818   0.03713   0.03131  -0.0776   0.6190   0.0114
 -12.500  -0.7734   0.03537   0.02943  -0.0781   0.6136   0.0116
 -12.000  -0.7535   0.03213   0.02593  -0.0789   0.6046   0.0121
 -11.750  -0.7420   0.03062   0.02430  -0.0792   0.6003   0.0123
 -11.500  -0.7294   0.02921   0.02274  -0.0794   0.5962   0.0125
 -11.250  -0.7156   0.02788   0.02127  -0.0796   0.5924   0.0128
 -11.000  -0.7006   0.02664   0.01991  -0.0799   0.5887   0.0130
 -10.750  -0.6861   0.02555   0.01870  -0.0798   0.5849   0.0131
 -10.500  -0.6705   0.02463   0.01765  -0.0796   0.5813   0.0133
 -10.250  -0.6521   0.02378   0.01666  -0.0794   0.5780   0.0135
 -10.000  -0.6356   0.02263   0.01544  -0.0791   0.5754   0.0138
  -9.750  -0.6163   0.02175   0.01450  -0.0789   0.5726   0.0140
  -9.500  -0.5953   0.02103   0.01372  -0.0788   0.5697   0.0143
  -9.250  -0.5733   0.02041   0.01304  -0.0788   0.5669   0.0146
  -9.000  -0.5505   0.01985   0.01241  -0.0787   0.5643   0.0150
  -8.750  -0.5274   0.01932   0.01180  -0.0787   0.5617   0.0154
  -8.500  -0.5038   0.01876   0.01119  -0.0787   0.5593   0.0159
  -8.250  -0.4797   0.01824   0.01060  -0.0787   0.5567   0.0164
  -8.000  -0.4554   0.01773   0.01002  -0.0787   0.5540   0.0168
  -7.750  -0.4310   0.01722   0.00943  -0.0787   0.5515   0.0171
  -7.500  -0.4067   0.01668   0.00881  -0.0786   0.5492   0.0174
  -7.250  -0.3827   0.01608   0.00816  -0.0786   0.5471   0.0179
  -7.000  -0.3574   0.01564   0.00766  -0.0787   0.5452   0.0185
  -6.750  -0.3313   0.01524   0.00723  -0.0788   0.5432   0.0192
  -6.500  -0.3049   0.01488   0.00683  -0.0790   0.5412   0.0199
  -6.250  -0.2782   0.01455   0.00645  -0.0791   0.5390   0.0208
  -6.000  -0.2512   0.01426   0.00610  -0.0793   0.5368   0.0217
  -5.750  -0.2246   0.01392   0.00572  -0.0795   0.5346   0.0232
  -5.500  -0.1975   0.01366   0.00542  -0.0796   0.5325   0.0251
  -5.250  -0.1702   0.01345   0.00514  -0.0798   0.5305   0.0274
  -5.000  -0.1427   0.01318   0.00487  -0.0801   0.5289   0.0312
  -4.750  -0.1150   0.01294   0.00462  -0.0803   0.5271   0.0367
  -4.500  -0.0875   0.01265   0.00437  -0.0806   0.5253   0.0472
  -4.250  -0.0607   0.01224   0.00409  -0.0809   0.5235   0.0803
  -4.000  -0.0342   0.01178   0.00381  -0.0811   0.5216   0.1302
  -3.750  -0.0083   0.01119   0.00351  -0.0814   0.5198   0.2080
  -3.500   0.0173   0.01056   0.00320  -0.0817   0.5180   0.2986
  -3.250   0.0429   0.01000   0.00299  -0.0819   0.5162   0.4081
  -3.000   0.0707   0.00984   0.00294  -0.0822   0.5145   0.4565
  -2.750   0.0992   0.00974   0.00292  -0.0825   0.5129   0.4865
  -2.500   0.1278   0.00970   0.00294  -0.0827   0.5113   0.5112
  -2.250   0.1568   0.00972   0.00297  -0.0830   0.5096   0.5331
  -2.000   0.1858   0.00973   0.00298  -0.0833   0.5080   0.5425
  -1.750   0.2151   0.00977   0.00295  -0.0837   0.5063   0.5493
  -1.500   0.2441   0.00979   0.00296  -0.0840   0.5047   0.5561
  -1.250   0.2733   0.00984   0.00296  -0.0844   0.5030   0.5638
  -1.000   0.3022   0.00989   0.00297  -0.0847   0.5013   0.5696
  -0.750   0.3311   0.00996   0.00299  -0.0851   0.4996   0.5749
  -0.500   0.3605   0.00999   0.00299  -0.0855   0.4982   0.5791
  -0.250   0.3897   0.01002   0.00301  -0.0859   0.4968   0.5828
   0.000   0.4188   0.01005   0.00305  -0.0863   0.4953   0.5865
   0.250   0.4479   0.01009   0.00309  -0.0867   0.4937   0.5903
   0.500   0.4771   0.01014   0.00311  -0.0871   0.4922   0.5941
   0.750   0.5062   0.01019   0.00314  -0.0875   0.4906   0.5975
   1.000   0.5350   0.01023   0.00318  -0.0878   0.4890   0.6007
   1.250   0.5638   0.01029   0.00323  -0.0882   0.4874   0.6043
   1.500   0.5927   0.01037   0.00328  -0.0885   0.4858   0.6080
   1.750   0.6215   0.01046   0.00334  -0.0889   0.4844   0.6114
   2.000   0.6505   0.01051   0.00342  -0.0893   0.4832   0.6144
   2.250   0.6793   0.01056   0.00351  -0.0897   0.4818   0.6174
   2.500   0.7081   0.01062   0.00360  -0.0901   0.4803   0.6209
   2.750   0.7369   0.01069   0.00369  -0.0905   0.4787   0.6244
   3.000   0.7656   0.01077   0.00377  -0.0909   0.4770   0.6277
   3.250   0.7942   0.01083   0.00386  -0.0912   0.4754   0.6305
   3.500   0.8226   0.01091   0.00396  -0.0915   0.4739   0.6335
   3.750   0.8510   0.01099   0.00407  -0.0919   0.4725   0.6369
   4.000   0.8794   0.01110   0.00418  -0.0922   0.4712   0.6404
   4.250   0.9078   0.01122   0.00430  -0.0926   0.4697   0.6437
   4.500   0.9361   0.01130   0.00444  -0.0929   0.4683   0.6465
   4.750   0.9643   0.01138   0.00459  -0.0932   0.4667   0.6497
   5.000   0.9925   0.01147   0.00475  -0.0935   0.4650   0.6532
   5.250   1.0206   0.01157   0.00490  -0.0939   0.4635   0.6568
   5.500   1.0487   0.01168   0.00505  -0.0942   0.4619   0.6602
   5.750   1.0765   0.01177   0.00521  -0.0944   0.4602   0.6635
   6.000   1.1042   0.01188   0.00537  -0.0947   0.4585   0.6671
   6.250   1.1319   0.01200   0.00553  -0.0949   0.4570   0.6710
   6.500   1.1595   0.01215   0.00571  -0.0952   0.4554   0.6751
   6.750   1.1867   0.01225   0.00591  -0.0954   0.4530   0.6789
   7.000   1.2137   0.01232   0.00609  -0.0955   0.4494   0.6831
   7.250   1.2404   0.01240   0.00623  -0.0956   0.4452   0.6875
   7.500   1.2665   0.01251   0.00635  -0.0956   0.4408   0.6921
   7.750   1.2925   0.01256   0.00652  -0.0956   0.4330   0.6964
   8.000   1.3172   0.01269   0.00666  -0.0953   0.4256   0.7010
   8.250   1.3431   0.01281   0.00689  -0.0953   0.4181   0.7061
   8.500   1.3673   0.01299   0.00710  -0.0950   0.4103   0.7112
   8.750   1.3911   0.01318   0.00736  -0.0947   0.3992   0.7168
   9.000   1.4137   0.01346   0.00767  -0.0942   0.3862   0.7226
   9.250   1.4316   0.01393   0.00810  -0.0930   0.3637   0.7283
   9.500   1.4365   0.01504   0.00902  -0.0900   0.3198   0.7351
   9.750   1.4256   0.01677   0.01051  -0.0848   0.2726   0.7426
  10.000   1.4021   0.01958   0.01310  -0.0793   0.2214   0.7514
  10.250   1.3707   0.02386   0.01719  -0.0754   0.1731   0.7607
  10.500   1.3422   0.02901   0.02224  -0.0736   0.1366   0.7709
  10.750   1.3153   0.03429   0.02747  -0.0723   0.1051   0.7821
  11.000   1.2950   0.03885   0.03202  -0.0710   0.0826   0.7958
  11.250   1.2807   0.04273   0.03593  -0.0698   0.0666   0.8170
  11.500   1.2687   0.04577   0.03924  -0.0681   0.0561   0.9963
  11.750   1.2633   0.04890   0.04237  -0.0673   0.0484   1.0002
  12.000   1.2605   0.05188   0.04536  -0.0667   0.0426   1.0002
  12.250   1.2590   0.05480   0.04830  -0.0662   0.0377   1.0002
  12.500   1.2605   0.05744   0.05097  -0.0659   0.0339   1.0002
  12.750   1.2610   0.06022   0.05377  -0.0655   0.0306   1.0002
  13.000   1.2633   0.06284   0.05642  -0.0653   0.0278   1.0002
  13.250   1.2654   0.06551   0.05913  -0.0650   0.0253   1.0002
  13.500   1.2671   0.06824   0.06189  -0.0648   0.0231   1.0002
  13.750   1.2705   0.07078   0.06447  -0.0646   0.0213   1.0002
  14.000   1.2729   0.07350   0.06721  -0.0645   0.0198   1.0002
  14.250   1.2754   0.07620   0.06993  -0.0644   0.0183   1.0002
  14.500   1.2791   0.07879   0.07259  -0.0643   0.0173   1.0002
  14.750   1.2825   0.08142   0.07525  -0.0643   0.0163   1.0002
  15.000   1.2853   0.08411   0.07798  -0.0643   0.0152   1.0002
  15.250   1.2870   0.08699   0.08091  -0.0643   0.0144   1.0002
  15.500   1.2917   0.08950   0.08349  -0.0644   0.0135   1.0002
  15.750   1.2956   0.09212   0.08616  -0.0645   0.0128   1.0002
  16.000   1.2982   0.09493   0.08901  -0.0646   0.0121   1.0002
  16.250   1.3007   0.09773   0.09185  -0.0648   0.0114   1.0002
<< Back to WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)

Polar data table (+)

Polar graphs


<< Back to WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA) (fx6617ai-il)