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GOE 654 AIRFOIL (goe654-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 654 AIRFOIL (goe654-il)
Reynolds number: 500,000
Max Cl/Cd: 94.35 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe654-il-500000.txt
Download as CSV file: xf-goe654-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 654 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.1275   0.10366   0.10161  -0.0491   0.9848   0.0305
 -10.750  -0.1192   0.09944   0.09738  -0.0520   0.9757   0.0317
 -10.500  -0.1343   0.09130   0.08922  -0.0596   0.9683   0.0331
 -10.250  -0.1212   0.08593   0.08384  -0.0628   0.9581   0.0335
 -10.000  -0.0929   0.08213   0.08001  -0.0670   0.9464   0.0339
  -9.750  -0.0637   0.07755   0.07539  -0.0731   0.9323   0.0344
  -9.500  -0.0354   0.07257   0.07032  -0.0800   0.9134   0.0355
  -9.250  -0.0202   0.06737   0.06499  -0.0858   0.8856   0.0372
  -9.000  -0.0564   0.05635   0.05389  -0.0941   0.8637   0.0391
  -8.750  -0.0488   0.05414   0.05156  -0.0936   0.8384   0.0394
  -8.500  -0.0439   0.05200   0.04933  -0.0932   0.8164   0.0397
  -8.250  -0.0399   0.04989   0.04714  -0.0929   0.7969   0.0401
  -8.000  -0.0431   0.04680   0.04399  -0.0936   0.7792   0.0403
  -7.750  -0.0488   0.04373   0.04088  -0.0945   0.7632   0.0409
  -7.500  -0.0754   0.03805   0.03513  -0.0989   0.7503   0.0410
  -7.250  -0.0848   0.03330   0.03023  -0.1011   0.7373   0.0417
  -7.000  -0.1277   0.02305   0.01912  -0.1031   0.7290   0.0458
  -6.750  -0.1098   0.02123   0.01731  -0.1027   0.7130   0.0464
  -6.500  -0.0934   0.03252   0.02829  -0.1084   0.7231   0.0469
  -6.250  -0.0750   0.03149   0.02716  -0.1075   0.7053   0.0478
  -6.000  -0.0572   0.03025   0.02575  -0.1066   0.6881   0.0494
  -5.750  -0.0471   0.02752   0.02244  -0.1048   0.6733   0.0542
  -5.500  -0.0260   0.02634   0.02120  -0.1042   0.6572   0.0551
  -5.250  -0.0048   0.02536   0.02011  -0.1034   0.6420   0.0564
  -5.000   0.0138   0.02474   0.01894  -0.1017   0.6288   0.0626
  -4.750   0.0358   0.02295   0.01717  -0.1013   0.6174   0.0640
  -4.500   0.0538   0.01664   0.00964  -0.0978   0.6096   0.0399
  -4.250   0.0795   0.01612   0.00894  -0.0971   0.6007   0.0393
  -4.000   0.1052   0.01558   0.00826  -0.0965   0.5924   0.0391
  -3.750   0.1309   0.01495   0.00752  -0.0959   0.5852   0.0391
  -3.500   0.1567   0.01433   0.00682  -0.0954   0.5782   0.0392
  -3.250   0.1819   0.01373   0.00613  -0.0947   0.5724   0.0394
  -3.000   0.2079   0.01321   0.00560  -0.0942   0.5668   0.0396
  -2.750   0.2333   0.01278   0.00514  -0.0936   0.5610   0.0401
  -2.500   0.2587   0.01250   0.00481  -0.0931   0.5556   0.0409
  -2.250   0.2849   0.01221   0.00453  -0.0926   0.5503   0.0418
  -2.000   0.3108   0.01196   0.00425  -0.0921   0.5452   0.0425
  -1.750   0.3367   0.01179   0.00401  -0.0915   0.5404   0.0431
  -1.500   0.3630   0.01161   0.00381  -0.0911   0.5359   0.0440
  -1.250   0.3896   0.01144   0.00363  -0.0907   0.5310   0.0448
  -1.000   0.4157   0.01130   0.00344  -0.0902   0.5260   0.0459
  -0.750   0.4419   0.01119   0.00328  -0.0897   0.5211   0.0480
  -0.500   0.4687   0.01106   0.00317  -0.0894   0.5160   0.0508
  -0.250   0.4952   0.01097   0.00308  -0.0890   0.5108   0.0561
   0.250   0.5420   0.00995   0.00304  -0.0876   0.5012   0.3779
   0.500   0.5650   0.00958   0.00309  -0.0866   0.4959   0.5179
   0.750   0.5861   0.00926   0.00315  -0.0852   0.4906   0.6516
   1.000   0.6552   0.00867   0.00334  -0.0934   0.4825   0.9748
   1.250   0.7108   0.00879   0.00334  -0.0993   0.4742   1.0000
   1.500   0.7343   0.00887   0.00336  -0.0984   0.4678   1.0000
   1.750   0.7578   0.00894   0.00338  -0.0974   0.4604   1.0000
   2.000   0.7809   0.00905   0.00341  -0.0964   0.4532   1.0000
   2.250   0.8045   0.00912   0.00345  -0.0954   0.4444   1.0000
   2.500   0.8276   0.00924   0.00349  -0.0944   0.4353   1.0000
   2.750   0.8503   0.00937   0.00355  -0.0934   0.4248   1.0000
   3.000   0.8735   0.00949   0.00362  -0.0924   0.4137   1.0000
   3.250   0.8959   0.00966   0.00371  -0.0913   0.4032   1.0000
   3.500   0.9178   0.00986   0.00382  -0.0901   0.3928   1.0000
   3.750   0.9406   0.01004   0.00395  -0.0891   0.3832   1.0000
   4.000   0.9624   0.01028   0.00410  -0.0879   0.3747   1.0000
   4.250   0.9851   0.01048   0.00426  -0.0869   0.3670   1.0000
   4.500   1.0066   0.01075   0.00444  -0.0858   0.3604   1.0000
   4.750   1.0300   0.01093   0.00462  -0.0849   0.3545   1.0000
   5.000   1.0520   0.01118   0.00481  -0.0839   0.3488   1.0000
   5.250   1.0739   0.01145   0.00503  -0.0828   0.3438   1.0000
   5.500   1.0973   0.01163   0.00523  -0.0820   0.3391   1.0000
   5.750   1.1194   0.01188   0.00544  -0.0810   0.3344   1.0000
   6.000   1.1400   0.01222   0.00572  -0.0798   0.3296   1.0000
   6.250   1.1634   0.01239   0.00592  -0.0790   0.3255   1.0000
   6.500   1.1854   0.01260   0.00613  -0.0780   0.3207   1.0000
   6.750   1.2059   0.01291   0.00640  -0.0768   0.3161   1.0000
   7.000   1.2270   0.01320   0.00668  -0.0757   0.3124   1.0000
   7.250   1.2493   0.01339   0.00692  -0.0748   0.3092   1.0000
   7.500   1.2705   0.01362   0.00717  -0.0737   0.3056   1.0000
   7.750   1.2894   0.01392   0.00744  -0.0723   0.3013   1.0000
   8.000   1.3068   0.01424   0.00775  -0.0705   0.2966   1.0000
   8.250   1.3262   0.01441   0.00798  -0.0691   0.2925   1.0000
   8.500   1.3440   0.01467   0.00825  -0.0675   0.2880   1.0000
   8.750   1.3599   0.01504   0.00859  -0.0656   0.2837   1.0000
   9.000   1.3781   0.01533   0.00892  -0.0641   0.2802   1.0000
   9.250   1.3971   0.01556   0.00921  -0.0628   0.2758   1.0000
   9.500   1.4140   0.01590   0.00957  -0.0612   0.2716   1.0000
   9.750   1.4280   0.01637   0.01002  -0.0593   0.2671   1.0000
  10.000   1.4472   0.01662   0.01035  -0.0582   0.2622   1.0000
  10.250   1.4629   0.01701   0.01076  -0.0566   0.2563   1.0000
  10.500   1.4761   0.01756   0.01131  -0.0547   0.2514   1.0000
  10.750   1.4940   0.01792   0.01174  -0.0536   0.2458   1.0000
  11.000   1.5068   0.01852   0.01234  -0.0519   0.2395   1.0000
  11.250   1.5211   0.01909   0.01295  -0.0504   0.2323   1.0000
  11.500   1.5316   0.01988   0.01373  -0.0487   0.2241   1.0000
  11.750   1.5420   0.02074   0.01458  -0.0470   0.2125   1.0000
  12.000   1.5501   0.02178   0.01562  -0.0453   0.2015   1.0000
  12.250   1.5539   0.02318   0.01696  -0.0434   0.1878   1.0000
  12.500   1.5537   0.02494   0.01867  -0.0414   0.1726   1.0000
  12.750   1.5534   0.02685   0.02054  -0.0397   0.1599   1.0000
  13.000   1.5424   0.02974   0.02332  -0.0377   0.1413   1.0000
  13.250   1.5362   0.03241   0.02596  -0.0363   0.1279   1.0000
  13.500   1.5287   0.03535   0.02887  -0.0351   0.1158   1.0000
  13.750   1.5140   0.03913   0.03259  -0.0341   0.0993   1.0000
  14.000   1.4944   0.04362   0.03702  -0.0334   0.0804   1.0000
  14.250   1.4681   0.04910   0.04243  -0.0330   0.0598   1.0000
  14.500   1.4440   0.05464   0.04796  -0.0331   0.0443   1.0000
  14.750   1.4174   0.06066   0.05399  -0.0335   0.0292   1.0000
  15.000   1.4016   0.06560   0.05898  -0.0339   0.0246   1.0000
  15.250   1.3901   0.07010   0.06357  -0.0345   0.0222   1.0000
  15.500   1.3815   0.07433   0.06789  -0.0350   0.0212   1.0000
  15.750   1.3736   0.07855   0.07222  -0.0357   0.0205   1.0000
  16.000   1.3646   0.08302   0.07679  -0.0366   0.0200   1.0000
  16.250   1.3535   0.08788   0.08176  -0.0376   0.0194   1.0000
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