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GOE 506 AIRFOIL (goe506-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 506 AIRFOIL (goe506-il)
Reynolds number: 100,000
Max Cl/Cd: 40.65 at α=8.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe506-il-100000-n5.txt
Download as CSV file: xf-goe506-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 506 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.2844   0.09544   0.09054  -0.0865   0.9639   0.0334
 -11.250  -0.3092   0.08483   0.07991  -0.0935   0.9601   0.0330
 -11.000  -0.3470   0.07355   0.06852  -0.1020   0.9532   0.0322
 -10.750  -0.3799   0.06313   0.05783  -0.1135   0.9475   0.0314
 -10.500  -0.4093   0.05842   0.05290  -0.1158   0.9376   0.0309
 -10.250  -0.4299   0.05522   0.04948  -0.1156   0.9308   0.0312
 -10.000  -0.4503   0.05314   0.04720  -0.1121   0.9221   0.0314
  -9.500  -0.4698   0.04846   0.04193  -0.1065   0.9083   0.0323
  -9.250  -0.4675   0.04588   0.03892  -0.1051   0.9038   0.0332
  -9.000  -0.4696   0.04410   0.03680  -0.1017   0.8981   0.0337
  -8.750  -0.4702   0.04255   0.03492  -0.0980   0.8921   0.0341
  -8.500  -0.4581   0.04055   0.03256  -0.0966   0.8889   0.0347
  -8.250  -0.4375   0.03866   0.03059  -0.0965   0.8869   0.0358
  -8.000  -0.4361   0.03791   0.02977  -0.0925   0.8807   0.0368
  -7.750  -0.4233   0.03687   0.02859  -0.0905   0.8763   0.0382
  -7.500  -0.4037   0.03565   0.02716  -0.0896   0.8737   0.0398
  -7.250  -0.3805   0.03442   0.02570  -0.0892   0.8718   0.0411
  -7.000  -0.3553   0.03327   0.02436  -0.0890   0.8703   0.0427
  -6.750  -0.3618   0.03297   0.02410  -0.0834   0.8631   0.0436
  -6.500  -0.3438   0.03217   0.02330  -0.0821   0.8599   0.0455
  -6.250  -0.3210   0.03138   0.02244  -0.0814   0.8575   0.0474
  -6.000  -0.2965   0.03064   0.02159  -0.0810   0.8558   0.0492
  -5.750  -0.2888   0.03046   0.02129  -0.0777   0.8513   0.0510
  -5.500  -0.2796   0.02997   0.02081  -0.0747   0.8462   0.0529
  -5.250  -0.2541   0.02924   0.02002  -0.0744   0.8427   0.0557
  -5.000  -0.2186   0.02834   0.01895  -0.0757   0.8399   0.0590
  -4.750  -0.2131   0.02819   0.01871  -0.0717   0.8312   0.0616
  -4.500  -0.1800   0.02720   0.01764  -0.0725   0.8268   0.0674
  -4.250  -0.1555   0.02660   0.01693  -0.0716   0.8211   0.0736
  -4.000  -0.1346   0.02585   0.01620  -0.0702   0.8137   0.0859
  -3.750  -0.1010   0.02455   0.01554  -0.0713   0.8103   0.2083
  -3.500  -0.0867   0.02452   0.01544  -0.0687   0.8008   0.2333
  -3.250  -0.0508   0.02394   0.01484  -0.0696   0.7962   0.2602
  -3.000  -0.0310   0.02382   0.01467  -0.0680   0.7887   0.2790
  -2.750  -0.0034   0.02347   0.01428  -0.0676   0.7828   0.2945
  -2.500   0.0318   0.02294   0.01371  -0.0685   0.7798   0.3117
  -2.250   0.0434   0.02310   0.01385  -0.0656   0.7710   0.3214
  -2.000   0.0733   0.02269   0.01344  -0.0657   0.7667   0.3387
  -1.750   0.1096   0.02206   0.01281  -0.0667   0.7638   0.3576
  -1.500   0.1194   0.02224   0.01301  -0.0635   0.7536   0.3697
  -1.250   0.1548   0.02160   0.01237  -0.0644   0.7495   0.3861
  -1.000   0.1708   0.02158   0.01236  -0.0622   0.7399   0.4012
  -0.750   0.2041   0.02096   0.01181  -0.0627   0.7342   0.4250
  -0.500   0.2225   0.02083   0.01176  -0.0609   0.7240   0.4528
  -0.250   0.2572   0.02016   0.01124  -0.0617   0.7176   0.5002
   0.250   0.2983   0.01949   0.01118  -0.0584   0.6953   0.6579
   0.500   0.4022   0.01864   0.01091  -0.0724   0.6844   0.8917
   0.750   0.4747   0.01873   0.01094  -0.0815   0.6633   0.9824
   1.000   0.5028   0.01882   0.01088  -0.0817   0.6387   1.0000
   1.250   0.5226   0.01865   0.01051  -0.0798   0.6060   1.0000
   1.500   0.5628   0.01812   0.00955  -0.0813   0.5649   1.0000
   1.750   0.5905   0.01809   0.00906  -0.0809   0.5301   1.0000
   2.000   0.6079   0.01836   0.00901  -0.0790   0.5054   1.0000
   2.250   0.6244   0.01868   0.00909  -0.0769   0.4860   1.0000
   2.500   0.6404   0.01902   0.00924  -0.0749   0.4694   1.0000
   2.750   0.6575   0.01934   0.00940  -0.0731   0.4560   1.0000
   3.000   0.6755   0.01966   0.00956  -0.0715   0.4444   1.0000
   3.250   0.6938   0.01997   0.00976  -0.0699   0.4343   1.0000
   3.500   0.7129   0.02028   0.00996  -0.0685   0.4255   1.0000
   3.750   0.7327   0.02058   0.01017  -0.0673   0.4177   1.0000
   4.000   0.7536   0.02088   0.01037  -0.0662   0.4112   1.0000
   4.250   0.7745   0.02118   0.01061  -0.0652   0.4051   1.0000
   4.500   0.7957   0.02150   0.01085  -0.0642   0.3995   1.0000
   4.750   0.8165   0.02182   0.01111  -0.0632   0.3938   1.0000
   5.000   0.8370   0.02215   0.01140  -0.0622   0.3882   1.0000
   5.250   0.8583   0.02250   0.01168  -0.0613   0.3834   1.0000
   5.500   0.8805   0.02284   0.01198  -0.0606   0.3794   1.0000
   5.750   0.9019   0.02318   0.01234  -0.0598   0.3753   1.0000
   6.000   0.9235   0.02354   0.01270  -0.0590   0.3714   1.0000
   6.250   0.9463   0.02391   0.01303  -0.0584   0.3682   1.0000
   6.500   0.9697   0.02429   0.01336  -0.0580   0.3649   1.0000
   6.750   0.9898   0.02469   0.01383  -0.0570   0.3612   1.0000
   7.000   1.0107   0.02510   0.01428  -0.0562   0.3577   1.0000
   7.250   1.0308   0.02552   0.01472  -0.0552   0.3538   1.0000
   7.500   1.0524   0.02594   0.01510  -0.0546   0.3500   1.0000
   7.750   1.0704   0.02641   0.01564  -0.0533   0.3458   1.0000
   8.000   1.0883   0.02689   0.01620  -0.0522   0.3420   1.0000
   8.250   1.1076   0.02737   0.01674  -0.0512   0.3385   1.0000
   8.500   1.1281   0.02784   0.01726  -0.0504   0.3354   1.0000
   8.750   1.1505   0.02830   0.01769  -0.0499   0.3319   1.0000
   9.000   1.1631   0.02891   0.01846  -0.0481   0.3277   1.0000
   9.250   1.1782   0.02950   0.01916  -0.0466   0.3236   1.0000
   9.500   1.1954   0.03006   0.01979  -0.0454   0.3200   1.0000
   9.750   1.2145   0.03060   0.02037  -0.0446   0.3166   1.0000
  10.000   1.2307   0.03123   0.02110  -0.0433   0.3130   1.0000
  10.250   1.2416   0.03199   0.02203  -0.0415   0.3088   1.0000
  10.500   1.2548   0.03270   0.02286  -0.0399   0.3047   1.0000
  10.750   1.2700   0.03334   0.02358  -0.0386   0.3007   1.0000
  11.000   1.2834   0.03407   0.02439  -0.0372   0.2965   1.0000
  11.250   1.2875   0.03510   0.02563  -0.0347   0.2909   1.0000
  11.500   1.2933   0.03597   0.02656  -0.0325   0.2844   1.0000
  11.750   1.2950   0.03711   0.02784  -0.0300   0.2776   1.0000
  12.000   1.2954   0.03831   0.02916  -0.0275   0.2697   1.0000
  12.250   1.2956   0.03970   0.03070  -0.0252   0.2617   1.0000
  12.500   1.2969   0.04107   0.03218  -0.0232   0.2542   1.0000
  12.750   1.2962   0.04278   0.03406  -0.0212   0.2451   1.0000
  13.000   1.2962   0.04450   0.03588  -0.0195   0.2369   1.0000
  13.250   1.2945   0.04647   0.03797  -0.0178   0.2276   1.0000
  13.500   1.2910   0.04874   0.04034  -0.0163   0.2169   1.0000
  13.750   1.2884   0.05109   0.04277  -0.0151   0.2084   1.0000
  14.000   1.2818   0.05388   0.04558  -0.0139   0.1993   1.0000
  14.250   1.2725   0.05712   0.04884  -0.0129   0.1908   1.0000
  14.500   1.2617   0.06073   0.05248  -0.0121   0.1839   1.0000
  14.750   1.2480   0.06488   0.05663  -0.0117   0.1776   1.0000
  15.000   1.2369   0.06900   0.06084  -0.0117   0.1730   1.0000
  15.250   1.2241   0.07356   0.06550  -0.0120   0.1683   1.0000
  15.500   1.2119   0.07814   0.07015  -0.0124   0.1642   1.0000
  15.750   1.1991   0.08295   0.07503  -0.0131   0.1593   1.0000
  16.000   1.1856   0.08812   0.08037  -0.0142   0.1545   1.0000
  16.250   1.1721   0.09320   0.08549  -0.0153   0.1486   1.0000
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