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GOE 617 AIRFOIL (goe617-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 617 AIRFOIL (goe617-il)
Reynolds number: 500,000
Max Cl/Cd: 72.15 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe617-il-500000-n5.txt
Download as CSV file: xf-goe617-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 617 AIRFOIL                                 
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -17.500  -0.9317   0.08815   0.08485  -0.0534   1.0000   0.0167
 -17.250  -0.9975   0.07272   0.06914  -0.0626   1.0000   0.0166
 -17.000  -1.0373   0.06220   0.05840  -0.0693   1.0000   0.0165
 -16.750  -1.0645   0.05434   0.05034  -0.0743   1.0000   0.0165
 -16.500  -1.0795   0.04883   0.04469  -0.0776   1.0000   0.0167
 -16.250  -1.0903   0.04445   0.04017  -0.0798   1.0000   0.0168
 -16.000  -1.0953   0.04120   0.03681  -0.0808   1.0000   0.0172
 -15.750  -1.1018   0.03816   0.03364  -0.0811   1.0000   0.0172
 -15.500  -1.1015   0.03607   0.03146  -0.0807   1.0000   0.0177
 -15.250  -1.1024   0.03407   0.02936  -0.0798   1.0000   0.0180
 -15.000  -1.1001   0.03250   0.02767  -0.0785   1.0000   0.0184
 -14.750  -1.0980   0.03103   0.02608  -0.0768   1.0000   0.0189
 -14.500  -1.0945   0.02977   0.02471  -0.0749   1.0000   0.0193
 -14.250  -1.0910   0.02861   0.02343  -0.0726   1.0000   0.0196
 -14.000  -1.0885   0.02750   0.02225  -0.0699   1.0000   0.0199
 -13.750  -1.0828   0.02669   0.02141  -0.0674   1.0000   0.0205
 -13.500  -1.0782   0.02590   0.02056  -0.0644   1.0000   0.0209
 -13.250  -1.0737   0.02519   0.01978  -0.0611   1.0000   0.0212
 -13.000  -1.0669   0.02468   0.01921  -0.0580   1.0000   0.0219
 -12.750  -1.0648   0.02410   0.01856  -0.0540   1.0000   0.0223
 -12.500  -1.0642   0.02365   0.01803  -0.0494   1.0000   0.0228
 -12.000  -1.0338   0.02244   0.01664  -0.0460   0.9971   0.0238
 -11.750  -1.0077   0.02162   0.01578  -0.0467   0.9937   0.0246
 -11.500  -0.9816   0.02104   0.01516  -0.0470   0.9901   0.0255
 -11.250  -0.9544   0.02042   0.01448  -0.0475   0.9866   0.0263
 -11.000  -0.9254   0.01984   0.01381  -0.0483   0.9838   0.0271
 -10.750  -0.9002   0.01927   0.01316  -0.0483   0.9790   0.0278
 -10.500  -0.8735   0.01864   0.01246  -0.0486   0.9748   0.0286
 -10.250  -0.8449   0.01798   0.01178  -0.0493   0.9718   0.0295
 -10.000  -0.8197   0.01749   0.01125  -0.0491   0.9648   0.0304
  -9.750  -0.7881   0.01697   0.01068  -0.0503   0.9602   0.0315
  -9.500  -0.7575   0.01648   0.01011  -0.0511   0.9545   0.0324
  -9.250  -0.7257   0.01603   0.00958  -0.0522   0.9494   0.0333
  -9.000  -0.6932   0.01540   0.00894  -0.0536   0.9451   0.0345
  -8.750  -0.6627   0.01494   0.00845  -0.0545   0.9389   0.0357
  -8.500  -0.6308   0.01451   0.00798  -0.0556   0.9328   0.0369
  -8.250  -0.5974   0.01409   0.00750  -0.0570   0.9273   0.0382
  -8.000  -0.5690   0.01374   0.00709  -0.0573   0.9190   0.0394
  -7.750  -0.5390   0.01333   0.00664  -0.0579   0.9121   0.0410
  -7.500  -0.5134   0.01303   0.00632  -0.0576   0.9036   0.0427
  -7.250  -0.4857   0.01275   0.00599  -0.0576   0.8960   0.0447
  -7.000  -0.4614   0.01250   0.00570  -0.0569   0.8878   0.0467
  -6.750  -0.4358   0.01226   0.00545  -0.0565   0.8800   0.0493
  -6.500  -0.4116   0.01206   0.00522  -0.0557   0.8719   0.0520
  -6.250  -0.3868   0.01187   0.00498  -0.0551   0.8639   0.0547
  -6.000  -0.3627   0.01168   0.00478  -0.0543   0.8561   0.0578
  -5.750  -0.3379   0.01154   0.00459  -0.0536   0.8479   0.0610
  -5.500  -0.3135   0.01139   0.00440  -0.0528   0.8397   0.0636
  -5.250  -0.2897   0.01120   0.00419  -0.0520   0.8310   0.0669
  -5.000  -0.2653   0.01105   0.00402  -0.0512   0.8228   0.0699
  -4.750  -0.2407   0.01094   0.00384  -0.0504   0.8135   0.0723
  -4.500  -0.2165   0.01079   0.00366  -0.0496   0.8044   0.0745
  -4.250  -0.1928   0.01062   0.00345  -0.0486   0.7948   0.0775
  -4.000  -0.1690   0.01047   0.00328  -0.0477   0.7839   0.0804
  -3.750  -0.1448   0.01035   0.00312  -0.0469   0.7731   0.0834
  -3.500  -0.1206   0.01027   0.00296  -0.0460   0.7610   0.0860
  -3.250  -0.0973   0.01012   0.00280  -0.0450   0.7472   0.0916
  -3.000  -0.0742   0.01000   0.00266  -0.0439   0.7313   0.0985
  -2.750  -0.0520   0.00985   0.00252  -0.0427   0.7137   0.1143
  -2.250  -0.0083   0.00954   0.00233  -0.0401   0.6802   0.1811
  -2.000   0.0149   0.00947   0.00225  -0.0391   0.6652   0.1984
  -1.750   0.0382   0.00939   0.00217  -0.0381   0.6514   0.2152
  -1.250   0.0793   0.00890   0.00200  -0.0352   0.6281   0.3298
  -1.000   0.0994   0.00866   0.00196  -0.0336   0.6164   0.4023
  -0.750   0.1203   0.00849   0.00192  -0.0321   0.6054   0.4525
  -0.500   0.1409   0.00835   0.00190  -0.0306   0.5954   0.4985
  -0.250   0.1606   0.00815   0.00188  -0.0289   0.5860   0.5569
   0.000   0.1786   0.00795   0.00187  -0.0267   0.5767   0.6201
   0.250   0.1964   0.00778   0.00187  -0.0244   0.5649   0.6799
   0.500   0.2151   0.00762   0.00190  -0.0223   0.5530   0.7392
   0.750   0.2367   0.00753   0.00199  -0.0207   0.5409   0.8041
   1.000   0.2656   0.00757   0.00212  -0.0207   0.5308   0.8504
   1.250   0.2963   0.00764   0.00222  -0.0212   0.5218   0.8762
   1.500   0.3272   0.00777   0.00233  -0.0217   0.5127   0.8940
   1.750   0.3621   0.00789   0.00244  -0.0232   0.5024   0.9052
   2.000   0.3938   0.00804   0.00255  -0.0239   0.4897   0.9145
   2.250   0.4238   0.00822   0.00267  -0.0243   0.4762   0.9248
   2.500   0.4613   0.00842   0.00283  -0.0264   0.4646   0.9324
   2.750   0.4918   0.00856   0.00294  -0.0269   0.4543   0.9380
   3.000   0.5193   0.00872   0.00305  -0.0268   0.4441   0.9441
   3.500   0.5864   0.00922   0.00344  -0.0292   0.4142   0.9559
   3.750   0.6196   0.00950   0.00363  -0.0304   0.3939   0.9597
   4.000   0.6542   0.00979   0.00383  -0.0320   0.3729   0.9625
   4.250   0.6847   0.01005   0.00401  -0.0327   0.3555   0.9661
   4.500   0.7072   0.01030   0.00419  -0.0317   0.3387   0.9713
   4.750   0.7390   0.01056   0.00437  -0.0328   0.3210   0.9727
   5.000   0.7694   0.01084   0.00457  -0.0336   0.3026   0.9746
   5.250   0.7981   0.01111   0.00477  -0.0340   0.2842   0.9770
   5.500   0.8240   0.01142   0.00499  -0.0339   0.2615   0.9800
   5.750   0.8461   0.01186   0.00527  -0.0331   0.2279   0.9834
   6.000   0.8722   0.01247   0.00564  -0.0334   0.1863   0.9853
   6.250   0.8994   0.01287   0.00596  -0.0337   0.1708   0.9874
   6.500   0.9265   0.01320   0.00625  -0.0340   0.1614   0.9897
   6.750   0.9526   0.01353   0.00656  -0.0340   0.1535   0.9921
   7.000   0.9790   0.01383   0.00686  -0.0341   0.1470   0.9941
   7.250   1.0074   0.01413   0.00715  -0.0346   0.1394   0.9958
   7.500   1.0353   0.01446   0.00746  -0.0351   0.1318   0.9978
   7.750   1.0627   0.01480   0.00779  -0.0355   0.1231   0.9995
   8.000   1.0802   0.01510   0.00808  -0.0338   0.1168   1.0000
   8.250   1.0899   0.01539   0.00836  -0.0305   0.1103   1.0000
   8.500   1.0955   0.01567   0.00863  -0.0264   0.1052   1.0000
   8.750   1.1000   0.01592   0.00889  -0.0220   0.1006   1.0000
   9.000   1.1048   0.01624   0.00921  -0.0178   0.0963   1.0000
   9.250   1.1118   0.01658   0.00956  -0.0141   0.0927   1.0000
   9.500   1.1199   0.01695   0.00994  -0.0107   0.0887   1.0000
   9.750   1.1276   0.01741   0.01039  -0.0074   0.0849   1.0000
  10.000   1.1368   0.01788   0.01087  -0.0044   0.0814   1.0000
  10.250   1.1476   0.01833   0.01136  -0.0018   0.0786   1.0000
  10.500   1.1578   0.01885   0.01190   0.0008   0.0760   1.0000
  10.750   1.1672   0.01946   0.01252   0.0033   0.0735   1.0000
  11.000   1.1765   0.02012   0.01321   0.0058   0.0711   1.0000
  11.250   1.1889   0.02068   0.01382   0.0077   0.0696   1.0000
  11.500   1.2006   0.02131   0.01451   0.0096   0.0679   1.0000
  11.750   1.2116   0.02203   0.01526   0.0115   0.0657   1.0000
  12.000   1.2214   0.02285   0.01611   0.0134   0.0634   1.0000
  12.250   1.2304   0.02377   0.01706   0.0152   0.0615   1.0000
  12.500   1.2418   0.02459   0.01793   0.0167   0.0598   1.0000
  12.750   1.2528   0.02547   0.01888   0.0182   0.0585   1.0000
  13.000   1.2630   0.02645   0.01990   0.0196   0.0561   1.0000
  13.250   1.2715   0.02757   0.02105   0.0209   0.0535   1.0000
  13.500   1.2801   0.02876   0.02227   0.0222   0.0514   1.0000
  13.750   1.2895   0.02992   0.02350   0.0233   0.0494   1.0000
  14.000   1.2977   0.03121   0.02485   0.0243   0.0467   1.0000
  14.250   1.3038   0.03273   0.02638   0.0253   0.0439   1.0000
  14.500   1.3109   0.03421   0.02793   0.0262   0.0406   1.0000
  14.750   1.3151   0.03602   0.02975   0.0270   0.0363   1.0000
  15.000   1.3167   0.03811   0.03184   0.0278   0.0303   1.0000
  15.250   1.3120   0.04088   0.03459   0.0284   0.0227   1.0000
  15.500   1.3084   0.04369   0.03743   0.0288   0.0194   1.0000
  15.750   1.3081   0.04626   0.04006   0.0291   0.0180   1.0000
  16.000   1.3049   0.04923   0.04311   0.0291   0.0166   1.0000
  16.250   1.3023   0.05224   0.04620   0.0290   0.0156   1.0000
  16.500   1.3012   0.05515   0.04919   0.0288   0.0150   1.0000
  16.750   1.2991   0.05823   0.05237   0.0284   0.0145   1.0000
  17.000   1.2959   0.06154   0.05578   0.0278   0.0141   1.0000
  17.250   1.2897   0.06530   0.05964   0.0271   0.0135   1.0000
  17.500   1.2833   0.06917   0.06360   0.0262   0.0131   1.0000
  17.750   1.2762   0.07324   0.06777   0.0251   0.0129   1.0000
  18.000   1.2686   0.07749   0.07213   0.0238   0.0127   1.0000
  18.250   1.2618   0.08170   0.07645   0.0225   0.0123   1.0000
  18.500   1.2532   0.08624   0.08110   0.0210   0.0122   1.0000
  18.750   1.2444   0.09090   0.08588   0.0193   0.0120   1.0000
  19.000   1.2346   0.09581   0.09091   0.0175   0.0118   1.0000
  19.250   1.2231   0.10102   0.09623   0.0154   0.0114   1.0000
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