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GOE 533 AIRFOIL (goe533-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 533 AIRFOIL (goe533-il)
Reynolds number: 200,000
Max Cl/Cd: 75.5 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe533-il-200000-n5.txt
Download as CSV file: xf-goe533-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 533 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2755   0.11928   0.11548  -0.0380   1.0000   0.0387
 -11.250  -0.2722   0.11645   0.11269  -0.0389   1.0000   0.0407
 -11.000  -0.2887   0.11126   0.10754  -0.0438   1.0000   0.0424
 -10.250  -0.2831   0.09969   0.09605  -0.0448   1.0000   0.0361
 -10.000  -0.2791   0.09725   0.09365  -0.0444   1.0000   0.0356
  -9.750  -0.2810   0.09402   0.09047  -0.0449   1.0000   0.0356
  -9.500  -0.2756   0.08905   0.08553  -0.0488   0.9904   0.0357
  -9.250  -0.2660   0.08354   0.08002  -0.0545   0.9777   0.0357
  -9.000  -0.2528   0.07836   0.07482  -0.0603   0.9633   0.0353
  -8.750  -0.2407   0.07203   0.06847  -0.0680   0.9447   0.0350
  -8.500  -0.2315   0.06371   0.06010  -0.0790   0.9197   0.0347
  -8.250  -0.2539   0.04686   0.04283  -0.1012   0.8778   0.0342
  -8.000  -0.2578   0.03920   0.03456  -0.1071   0.8472   0.0347
  -7.750  -0.2503   0.03447   0.02924  -0.1090   0.8207   0.0349
  -7.250  -0.2188   0.02863   0.02236  -0.1095   0.7778   0.0355
  -7.000  -0.1988   0.02662   0.01988  -0.1093   0.7601   0.0358
  -6.750  -0.1770   0.02510   0.01783  -0.1090   0.7445   0.0364
  -6.500  -0.1541   0.02375   0.01628  -0.1087   0.7306   0.0370
  -6.250  -0.1299   0.02276   0.01511  -0.1084   0.7184   0.0375
  -6.000  -0.1053   0.02180   0.01393  -0.1081   0.7078   0.0379
  -5.750  -0.0801   0.02091   0.01284  -0.1078   0.6977   0.0382
  -5.500  -0.0545   0.02012   0.01186  -0.1075   0.6891   0.0387
  -5.250  -0.0286   0.01939   0.01097  -0.1071   0.6804   0.0392
  -5.000  -0.0025   0.01873   0.01014  -0.1068   0.6730   0.0397
  -4.750   0.0238   0.01812   0.00941  -0.1065   0.6651   0.0403
  -4.500   0.0502   0.01763   0.00877  -0.1061   0.6581   0.0412
  -4.250   0.0769   0.01719   0.00821  -0.1058   0.6511   0.0421
  -4.000   0.1034   0.01670   0.00765  -0.1055   0.6441   0.0428
  -3.750   0.1295   0.01619   0.00710  -0.1052   0.6379   0.0435
  -3.500   0.1560   0.01576   0.00667  -0.1049   0.6311   0.0443
  -3.250   0.1825   0.01542   0.00628  -0.1046   0.6246   0.0452
  -3.000   0.2093   0.01512   0.00593  -0.1044   0.6187   0.0463
  -2.750   0.2363   0.01483   0.00562  -0.1042   0.6122   0.0475
  -2.500   0.2634   0.01462   0.00533  -0.1039   0.6062   0.0490
  -2.250   0.2905   0.01437   0.00504  -0.1038   0.6007   0.0513
  -2.000   0.3178   0.01415   0.00482  -0.1036   0.5943   0.0539
  -1.750   0.3451   0.01400   0.00459  -0.1034   0.5881   0.0569
  -1.500   0.3725   0.01384   0.00440  -0.1032   0.5823   0.0615
  -1.250   0.3999   0.01364   0.00428  -0.1031   0.5758   0.0731
  -1.000   0.4270   0.01337   0.00416  -0.1030   0.5698   0.1256
  -0.750   0.4529   0.01272   0.00407  -0.1031   0.5638   0.2920
  -0.500   0.4784   0.01233   0.00419  -0.1028   0.5568   0.4530
  -0.250   0.5048   0.01227   0.00422  -0.1023   0.5506   0.5154
   0.000   0.5308   0.01219   0.00433  -0.1018   0.5438   0.5711
   0.250   0.5560   0.01218   0.00449  -0.1009   0.5370   0.6348
   0.500   0.5818   0.01223   0.00456  -0.1003   0.5309   0.6763
   0.750   0.6085   0.01225   0.00460  -0.0998   0.5232   0.6956
   1.000   0.6349   0.01229   0.00459  -0.0994   0.5163   0.7121
   1.250   0.6613   0.01231   0.00464  -0.0989   0.5085   0.7301
   1.500   0.6872   0.01232   0.00465  -0.0984   0.5009   0.7487
   1.750   0.7128   0.01233   0.00469  -0.0978   0.4927   0.7685
   2.000   0.7379   0.01235   0.00471  -0.0970   0.4843   0.7906
   2.250   0.7636   0.01235   0.00476  -0.0964   0.4757   0.8192
   2.500   0.7910   0.01230   0.00478  -0.0960   0.4671   0.8792
   2.750   0.8263   0.01237   0.00484  -0.0976   0.4581   1.0000
   3.000   0.8526   0.01256   0.00494  -0.0974   0.4504   1.0000
   3.250   0.8794   0.01275   0.00508  -0.0972   0.4432   1.0000
   3.500   0.9056   0.01296   0.00521  -0.0969   0.4359   1.0000
   3.750   0.9317   0.01317   0.00537  -0.0966   0.4290   1.0000
   4.000   0.9577   0.01339   0.00555  -0.0963   0.4219   1.0000
   4.250   0.9832   0.01364   0.00572  -0.0959   0.4158   1.0000
   4.500   1.0093   0.01385   0.00594  -0.0957   0.4092   1.0000
   4.750   1.0347   0.01410   0.00615  -0.0953   0.4032   1.0000
   5.000   1.0599   0.01436   0.00638  -0.0949   0.3973   1.0000
   5.250   1.0851   0.01460   0.00663  -0.0944   0.3905   1.0000
   5.500   1.1095   0.01489   0.00686  -0.0939   0.3842   1.0000
   5.750   1.1344   0.01514   0.00714  -0.0935   0.3778   1.0000
   6.000   1.1586   0.01542   0.00742  -0.0929   0.3713   1.0000
   6.250   1.1824   0.01573   0.00770  -0.0923   0.3660   1.0000
   6.500   1.2069   0.01600   0.00802  -0.0918   0.3604   1.0000
   6.750   1.2306   0.01630   0.00835  -0.0912   0.3549   1.0000
   7.000   1.2533   0.01665   0.00867  -0.0905   0.3495   1.0000
   7.250   1.2766   0.01693   0.00902  -0.0898   0.3426   1.0000
   7.500   1.2981   0.01729   0.00937  -0.0889   0.3352   1.0000
   7.750   1.3197   0.01762   0.00975  -0.0880   0.3279   1.0000
   8.000   1.3402   0.01799   0.01014  -0.0869   0.3200   1.0000
   8.250   1.3604   0.01838   0.01055  -0.0858   0.3125   1.0000
   8.500   1.3800   0.01877   0.01099  -0.0846   0.3050   1.0000
   8.750   1.3985   0.01920   0.01144  -0.0833   0.2981   1.0000
   9.000   1.4165   0.01962   0.01192  -0.0819   0.2897   1.0000
   9.250   1.4313   0.02010   0.01242  -0.0800   0.2814   1.0000
   9.500   1.4446   0.02061   0.01296  -0.0779   0.2718   1.0000
   9.750   1.4584   0.02115   0.01355  -0.0759   0.2635   1.0000
  10.000   1.4697   0.02179   0.01421  -0.0737   0.2551   1.0000
  10.250   1.4822   0.02244   0.01492  -0.0718   0.2463   1.0000
  10.500   1.4916   0.02324   0.01575  -0.0696   0.2377   1.0000
  10.750   1.5003   0.02412   0.01666  -0.0675   0.2282   1.0000
  11.000   1.5080   0.02513   0.01769  -0.0654   0.2192   1.0000
  11.250   1.5126   0.02636   0.01893  -0.0633   0.2100   1.0000
  11.500   1.5171   0.02770   0.02029  -0.0613   0.2013   1.0000
  11.750   1.5215   0.02916   0.02179  -0.0596   0.1950   1.0000
  12.000   1.5267   0.03066   0.02336  -0.0581   0.1894   1.0000
  12.250   1.5285   0.03250   0.02523  -0.0567   0.1841   1.0000
  12.500   1.5333   0.03422   0.02703  -0.0556   0.1791   1.0000
  12.750   1.5355   0.03624   0.02911  -0.0545   0.1734   1.0000
  13.000   1.5333   0.03873   0.03163  -0.0536   0.1679   1.0000
  13.250   1.5362   0.04089   0.03389  -0.0529   0.1609   1.0000
  13.500   1.5311   0.04389   0.03691  -0.0524   0.1538   1.0000
  13.750   1.5334   0.04626   0.03940  -0.0520   0.1460   1.0000
  14.000   1.5289   0.04940   0.04258  -0.0517   0.1378   1.0000
  14.250   1.5262   0.05248   0.04573  -0.0517   0.1247   1.0000
  14.500   1.5165   0.05644   0.04968  -0.0518   0.1051   1.0000
  15.000   1.4853   0.06635   0.05950  -0.0531   0.0855   1.0000
  15.250   1.4728   0.07121   0.06438  -0.0540   0.0807   1.0000
  15.500   1.4638   0.07574   0.06900  -0.0549   0.0768   1.0000
  15.750   1.4540   0.08052   0.07385  -0.0560   0.0738   1.0000
  16.000   1.4434   0.08556   0.07897  -0.0574   0.0713   1.0000
  16.250   1.4388   0.08981   0.08333  -0.0585   0.0690   1.0000
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