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GOE 572 AIRFOIL (goe572-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: GOE 572 AIRFOIL (goe572-il)
Reynolds number: 1,000,000
Max Cl/Cd: 98.64 at α=3.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe572-il-1000000-n5.txt
Download as CSV file: xf-goe572-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 572 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.3926   0.02960   0.02542  -0.1670   0.5938   0.0086
 -13.250  -0.4167   0.02694   0.02253  -0.1614   0.5874   0.0086
 -13.000  -0.4286   0.02541   0.02085  -0.1560   0.5817   0.0088
 -12.750  -0.4279   0.02428   0.01956  -0.1523   0.5729   0.0087
 -12.500  -0.4291   0.02289   0.01802  -0.1482   0.5666   0.0089
 -12.250  -0.4246   0.02179   0.01678  -0.1448   0.5603   0.0092
 -12.000  -0.4148   0.02102   0.01589  -0.1420   0.5542   0.0094
 -11.750  -0.4047   0.02018   0.01494  -0.1391   0.5476   0.0096
 -11.500  -0.3922   0.01953   0.01416  -0.1366   0.5414   0.0097
 -11.250  -0.3786   0.01889   0.01341  -0.1341   0.5361   0.0100
 -11.000  -0.3635   0.01832   0.01274  -0.1319   0.5309   0.0102
 -10.750  -0.3480   0.01779   0.01209  -0.1296   0.5254   0.0104
 -10.500  -0.3312   0.01733   0.01153  -0.1275   0.5208   0.0108
 -10.250  -0.3139   0.01686   0.01095  -0.1255   0.5155   0.0110
 -10.000  -0.2964   0.01641   0.01041  -0.1235   0.5106   0.0112
  -9.500  -0.2600   0.01557   0.00941  -0.1197   0.5019   0.0120
  -9.250  -0.2403   0.01523   0.00900  -0.1181   0.4973   0.0125
  -9.000  -0.2206   0.01492   0.00861  -0.1164   0.4928   0.0130
  -8.750  -0.2006   0.01465   0.00826  -0.1147   0.4882   0.0135
  -8.500  -0.1798   0.01435   0.00789  -0.1132   0.4841   0.0140
  -8.250  -0.1591   0.01407   0.00755  -0.1117   0.4803   0.0146
  -8.000  -0.1376   0.01388   0.00732  -0.1103   0.4760   0.0153
  -7.750  -0.1165   0.01370   0.00708  -0.1088   0.4718   0.0159
  -7.500  -0.0946   0.01348   0.00681  -0.1075   0.4679   0.0166
  -7.250  -0.0729   0.01329   0.00654  -0.1061   0.4641   0.0172
  -7.000  -0.0515   0.01310   0.00631  -0.1046   0.4601   0.0178
  -6.750  -0.0296   0.01299   0.00616  -0.1033   0.4564   0.0185
  -6.500  -0.0069   0.01287   0.00602  -0.1021   0.4534   0.0193
  -6.250   0.0155   0.01273   0.00584  -0.1009   0.4499   0.0200
  -6.000   0.0375   0.01260   0.00564  -0.0995   0.4461   0.0206
  -5.750   0.0589   0.01250   0.00547  -0.0981   0.4414   0.0212
  -5.500   0.0808   0.01239   0.00534  -0.0967   0.4378   0.0220
  -5.250   0.1028   0.01229   0.00523  -0.0954   0.4346   0.0227
  -5.000   0.1238   0.01218   0.00509  -0.0939   0.4313   0.0233
  -4.750   0.1442   0.01210   0.00496  -0.0922   0.4275   0.0240
  -4.500   0.1643   0.01206   0.00485  -0.0905   0.4233   0.0248
  -4.250   0.1853   0.01194   0.00470  -0.0889   0.4195   0.0252
  -4.000   0.2061   0.01184   0.00456  -0.0873   0.4160   0.0256
  -3.750   0.2256   0.01167   0.00435  -0.0855   0.4126   0.0264
  -3.500   0.2463   0.01162   0.00428  -0.0840   0.4090   0.0274
  -3.250   0.2675   0.01156   0.00419  -0.0825   0.4060   0.0281
  -3.000   0.2890   0.01148   0.00409  -0.0811   0.4024   0.0289
  -2.750   0.3102   0.01142   0.00399  -0.0797   0.3990   0.0295
  -2.500   0.3305   0.01139   0.00391  -0.0781   0.3945   0.0300
  -2.250   0.3507   0.01135   0.00382  -0.0765   0.3908   0.0304
  -2.000   0.3720   0.01129   0.00374  -0.0751   0.3879   0.0312
  -1.750   0.3929   0.01123   0.00365  -0.0736   0.3845   0.0320
  -1.500   0.4133   0.01123   0.00362  -0.0721   0.3799   0.0328
  -1.250   0.4337   0.01125   0.00361  -0.0705   0.3755   0.0336
  -1.000   0.4556   0.01123   0.00358  -0.0693   0.3733   0.0345
  -0.750   0.4770   0.01125   0.00357  -0.0680   0.3695   0.0356
  -0.500   0.4975   0.01129   0.00357  -0.0665   0.3654   0.0362
   0.000   0.5386   0.01137   0.00361  -0.0636   0.3568   0.0394
   0.250   0.5598   0.01141   0.00364  -0.0624   0.3534   0.0411
   0.500   0.5801   0.01149   0.00368  -0.0609   0.3491   0.0429
   0.750   0.6007   0.01155   0.00374  -0.0596   0.3464   0.0477
   1.000   0.6218   0.01160   0.00379  -0.0583   0.3437   0.0529
   1.250   0.6430   0.01164   0.00386  -0.0571   0.3406   0.0614
   1.500   0.6639   0.01170   0.00394  -0.0559   0.3374   0.0729
   1.750   0.6847   0.01177   0.00403  -0.0547   0.3345   0.0892
   2.000   0.7044   0.01187   0.00416  -0.0534   0.3309   0.1118
   2.250   0.7266   0.01187   0.00427  -0.0525   0.3288   0.1589
   2.500   0.7492   0.01185   0.00441  -0.0518   0.3264   0.2228
   2.750   0.7758   0.01167   0.00461  -0.0522   0.3227   0.3880
   3.250   1.1561   0.01172   0.00582  -0.1248   0.3080   1.0000
   3.500   1.1719   0.01189   0.00596  -0.1226   0.3054   1.0000
   3.750   1.1877   0.01207   0.00612  -0.1205   0.3030   1.0000
   4.000   1.2042   0.01226   0.00629  -0.1186   0.3006   1.0000
   4.250   1.2221   0.01242   0.00645  -0.1169   0.2990   1.0000
   4.500   1.2395   0.01259   0.00662  -0.1152   0.2971   1.0000
   4.750   1.2569   0.01278   0.00680  -0.1135   0.2951   1.0000
   5.000   1.2738   0.01300   0.00701  -0.1117   0.2927   1.0000
   5.250   1.2897   0.01325   0.00724  -0.1098   0.2903   1.0000
   5.500   1.3055   0.01352   0.00750  -0.1080   0.2879   1.0000
   5.750   1.3213   0.01379   0.00777  -0.1062   0.2856   1.0000
   6.000   1.3386   0.01403   0.00802  -0.1046   0.2843   1.0000
   6.250   1.3559   0.01428   0.00828  -0.1031   0.2827   1.0000
   6.500   1.3724   0.01457   0.00858  -0.1015   0.2810   1.0000
   6.750   1.3884   0.01489   0.00890  -0.0999   0.2788   1.0000
   7.000   1.4035   0.01526   0.00927  -0.0982   0.2765   1.0000
   7.250   1.4156   0.01576   0.00976  -0.0961   0.2724   1.0000
   7.500   1.4306   0.01617   0.01018  -0.0945   0.2704   1.0000
   7.750   1.4458   0.01659   0.01062  -0.0931   0.2675   1.0000
   8.000   1.4604   0.01707   0.01111  -0.0915   0.2650   1.0000
   8.250   1.4681   0.01788   0.01188  -0.0892   0.2580   1.0000
   8.500   1.4808   0.01850   0.01251  -0.0876   0.2555   1.0000
   8.750   1.4940   0.01912   0.01316  -0.0861   0.2524   1.0000
   9.000   1.5018   0.02006   0.01407  -0.0841   0.2460   1.0000
   9.250   1.5089   0.02110   0.01511  -0.0821   0.2412   1.0000
   9.500   1.5182   0.02205   0.01607  -0.0805   0.2361   1.0000
   9.750   1.5192   0.02358   0.01757  -0.0782   0.2283   1.0000
  10.000   1.5260   0.02482   0.01884  -0.0767   0.2239   1.0000
  10.250   1.5316   0.02621   0.02023  -0.0751   0.2193   1.0000
  10.500   1.5294   0.02822   0.02224  -0.0731   0.2127   1.0000
  10.750   1.5278   0.03030   0.02433  -0.0714   0.2051   1.0000
  11.000   1.5221   0.03282   0.02684  -0.0695   0.1983   1.0000
  11.250   1.5121   0.03580   0.02982  -0.0677   0.1892   1.0000
  11.750   1.4664   0.04460   0.03860  -0.0634   0.1627   1.0000
  12.000   1.4297   0.05066   0.04465  -0.0613   0.1422   1.0000
  12.250   1.4064   0.05562   0.04964  -0.0599   0.1295   1.0000
  12.500   1.3729   0.06183   0.05590  -0.0584   0.1127   1.0000
  12.750   1.3472   0.06743   0.06155  -0.0575   0.1004   1.0000
  13.000   1.3336   0.07173   0.06590  -0.0569   0.0932   1.0000
  13.250   1.3027   0.07824   0.07243  -0.0562   0.0756   1.0000
  13.500   1.2688   0.08531   0.07948  -0.0557   0.0535   1.0000
  13.750   1.2429   0.09160   0.08580  -0.0555   0.0367   1.0000
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