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GOE 562 AIRFOIL (goe562-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 562 AIRFOIL (goe562-il)
Reynolds number: 500,000
Max Cl/Cd: 96.65 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe562-il-500000-n5.txt
Download as CSV file: xf-goe562-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 562 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750   0.0146   0.09025   0.08659  -0.1145   0.7199   0.0120
 -10.500   0.0220   0.08728   0.08351  -0.1165   0.6987   0.0127
 -10.250   0.0249   0.08359   0.07974  -0.1184   0.6823   0.0132
 -10.000   0.0265   0.07983   0.07592  -0.1203   0.6687   0.0133
  -9.750   0.0235   0.07539   0.07146  -0.1226   0.6601   0.0141
  -9.500   0.0312   0.07320   0.06920  -0.1238   0.6473   0.0142
  -9.250   0.0369   0.07074   0.06671  -0.1251   0.6375   0.0145
  -9.000   0.0402   0.06797   0.06392  -0.1265   0.6312   0.0147
  -8.750   0.0419   0.06517   0.06111  -0.1279   0.6227   0.0152
  -8.500   0.0343   0.06136   0.05730  -0.1300   0.6170   0.0155
  -8.250   0.0203   0.05773   0.05369  -0.1306   0.6119   0.0156
  -8.000   0.0020   0.05310   0.04903  -0.1309   0.6073   0.0162
  -7.750  -0.0352   0.04399   0.03975  -0.1305   0.6047   0.0173
  -7.500  -0.0238   0.04281   0.03849  -0.1295   0.5989   0.0177
  -7.250  -0.0143   0.04108   0.03668  -0.1282   0.5934   0.0180
  -6.750  -0.0580   0.02635   0.02094  -0.1166   0.5872   0.0213
  -6.500  -0.0405   0.02594   0.02044  -0.1151   0.5817   0.0216
  -6.250  -0.0233   0.02531   0.01970  -0.1134   0.5760   0.0219
  -6.000  -0.0068   0.02453   0.01878  -0.1116   0.5708   0.0222
  -5.750   0.0104   0.02382   0.01793  -0.1098   0.5658   0.0227
  -5.500   0.0263   0.02269   0.01663  -0.1077   0.5612   0.0234
  -5.250   0.0400   0.02112   0.01478  -0.1050   0.5565   0.0245
  -5.000   0.0525   0.01921   0.01246  -0.1019   0.5522   0.0256
  -4.750   0.0710   0.01821   0.01118  -0.0999   0.5475   0.0261
  -4.500   0.0895   0.01721   0.01002  -0.0981   0.5426   0.0268
  -4.250   0.1105   0.01675   0.00946  -0.0968   0.5377   0.0272
  -4.000   0.1324   0.01630   0.00890  -0.0956   0.5334   0.0276
  -3.750   0.1549   0.01581   0.00831  -0.0945   0.5290   0.0281
  -3.500   0.1773   0.01530   0.00768  -0.0933   0.5244   0.0285
  -3.250   0.1998   0.01491   0.00717  -0.0922   0.5201   0.0290
  -3.000   0.2234   0.01448   0.00667  -0.0912   0.5156   0.0296
  -2.750   0.2465   0.01417   0.00626  -0.0902   0.5098   0.0304
  -2.500   0.2691   0.01383   0.00582  -0.0890   0.5046   0.0309
  -2.250   0.2928   0.01349   0.00541  -0.0881   0.4999   0.0314
  -2.000   0.3160   0.01318   0.00503  -0.0871   0.4951   0.0316
  -1.750   0.3387   0.01296   0.00475  -0.0860   0.4907   0.0320
  -1.500   0.3618   0.01281   0.00454  -0.0849   0.4868   0.0324
  -1.250   0.3839   0.01245   0.00415  -0.0837   0.4822   0.0328
  -1.000   0.4043   0.01222   0.00387  -0.0821   0.4756   0.0333
  -0.750   0.4253   0.01205   0.00368  -0.0807   0.4708   0.0342
  -0.500   0.4474   0.01193   0.00355  -0.0794   0.4666   0.0350
  -0.250   0.4691   0.01183   0.00344  -0.0781   0.4626   0.0360
   0.000   0.4902   0.01177   0.00333  -0.0767   0.4588   0.0367
   0.250   0.5119   0.01169   0.00323  -0.0754   0.4547   0.0376
   0.500   0.5340   0.01162   0.00315  -0.0741   0.4503   0.0386
   0.750   0.5551   0.01159   0.00307  -0.0727   0.4452   0.0395
   1.000   0.5763   0.01158   0.00303  -0.0713   0.4412   0.0403
   1.250   0.5986   0.01151   0.00296  -0.0702   0.4366   0.0427
   1.500   0.6201   0.01151   0.00294  -0.0689   0.4313   0.0446
   1.750   0.6413   0.01155   0.00295  -0.0675   0.4272   0.0484
   2.000   0.6636   0.01155   0.00296  -0.0664   0.4234   0.0548
   2.250   0.6859   0.01155   0.00299  -0.0653   0.4198   0.0698
   2.500   0.7021   0.01086   0.00322  -0.0634   0.4161   0.4395
   3.000   1.0132   0.01104   0.00443  -0.1218   0.3963   1.0000
   3.250   1.0346   0.01115   0.00452  -0.1206   0.3924   1.0000
   3.500   1.0558   0.01126   0.00462  -0.1193   0.3878   1.0000
   3.750   1.0761   0.01141   0.00474  -0.1179   0.3831   1.0000
   4.000   1.0960   0.01156   0.00486  -0.1164   0.3789   1.0000
   4.250   1.1168   0.01168   0.00498  -0.1151   0.3740   1.0000
   4.500   1.1363   0.01183   0.00512  -0.1135   0.3687   1.0000
   4.750   1.1547   0.01200   0.00527  -0.1118   0.3636   1.0000
   5.000   1.1732   0.01214   0.00541  -0.1100   0.3580   1.0000
   5.250   1.1893   0.01232   0.00557  -0.1077   0.3520   1.0000
   5.500   1.2062   0.01248   0.00574  -0.1057   0.3458   1.0000
   5.750   1.2222   0.01267   0.00591  -0.1034   0.3388   1.0000
   6.000   1.2382   0.01288   0.00611  -0.1012   0.3315   1.0000
   6.250   1.2516   0.01317   0.00634  -0.0985   0.3199   1.0000
   6.500   1.2660   0.01344   0.00660  -0.0961   0.3100   1.0000
   6.750   1.2782   0.01380   0.00690  -0.0933   0.2968   1.0000
   7.000   1.2922   0.01411   0.00719  -0.0908   0.2887   1.0000
   7.250   1.3023   0.01456   0.00758  -0.0877   0.2761   1.0000
   7.500   1.3144   0.01497   0.00797  -0.0850   0.2665   1.0000
   7.750   1.3238   0.01548   0.00843  -0.0819   0.2550   1.0000
   8.250   1.3466   0.01641   0.00933  -0.0766   0.2407   1.0000
   8.500   1.3583   0.01688   0.00982  -0.0741   0.2354   1.0000
   8.750   1.3682   0.01745   0.01038  -0.0714   0.2288   1.0000
   9.000   1.3778   0.01805   0.01097  -0.0687   0.2210   1.0000
   9.250   1.3858   0.01875   0.01166  -0.0659   0.2146   1.0000
   9.500   1.3971   0.01933   0.01228  -0.0637   0.2089   1.0000
   9.750   1.4018   0.02028   0.01320  -0.0607   0.2007   1.0000
  10.000   1.4120   0.02100   0.01396  -0.0586   0.1930   1.0000
  10.250   1.4162   0.02210   0.01504  -0.0560   0.1810   1.0000
  10.500   1.3959   0.02482   0.01751  -0.0510   0.1334   1.0000
  10.750   1.3676   0.02855   0.02110  -0.0463   0.0947   1.0000
  11.000   1.3459   0.03227   0.02475  -0.0431   0.0629   1.0000
  11.250   1.3428   0.03469   0.02721  -0.0415   0.0535   1.0000
  11.500   1.3386   0.03734   0.02988  -0.0401   0.0441   1.0000
  11.750   1.3276   0.04074   0.03327  -0.0387   0.0244   1.0000
  12.000   1.3193   0.04399   0.03653  -0.0375   0.0183   1.0000
  12.250   1.3151   0.04690   0.03951  -0.0366   0.0160   1.0000
  12.500   1.3133   0.04961   0.04231  -0.0359   0.0149   1.0000
  12.750   1.3120   0.05235   0.04515  -0.0353   0.0141   1.0000
  13.000   1.3093   0.05527   0.04815  -0.0347   0.0133   1.0000
  13.250   1.3062   0.05829   0.05126  -0.0342   0.0128   1.0000
  13.500   1.2994   0.06183   0.05489  -0.0338   0.0119   1.0000
  13.750   1.2938   0.06530   0.05845  -0.0335   0.0114   1.0000
  14.000   1.2902   0.06857   0.06181  -0.0333   0.0112   1.0000
  14.250   1.2867   0.07190   0.06523  -0.0332   0.0109   1.0000
  14.500   1.2824   0.07536   0.06879  -0.0332   0.0106   1.0000
  14.750   1.2773   0.07901   0.07254  -0.0332   0.0104   1.0000
  15.000   1.2723   0.08266   0.07629  -0.0333   0.0102   1.0000
  15.250   1.2670   0.08639   0.08009  -0.0336   0.0094   1.0000
  15.500   1.2608   0.09032   0.08412  -0.0338   0.0097   1.0000
  15.750   1.2534   0.09447   0.08836  -0.0342   0.0092   1.0000
  16.000   1.2464   0.09859   0.09256  -0.0347   0.0090   1.0000
  16.250   1.2372   0.10309   0.09716  -0.0352   0.0089   1.0000
  16.500   1.2294   0.10740   0.10154  -0.0359   0.0086   1.0000
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