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GOE 481A AIRFOIL (goe481a-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 481A AIRFOIL (goe481a-il)
Reynolds number: 500,000
Max Cl/Cd: 80.16 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe481a-il-500000.txt
Download as CSV file: xf-goe481a-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 481A 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.0691   0.09413   0.09144  -0.0901   0.9522   0.0597
  -8.500  -0.0586   0.09112   0.08843  -0.0923   0.9496   0.0609
  -8.250  -0.3908   0.03184   0.02769  -0.1188   0.9190   0.0560
  -8.000  -0.3763   0.02836   0.02371  -0.1189   0.9174   0.0566
  -7.750  -0.3784   0.02719   0.02231  -0.1138   0.9086   0.0569
  -7.500  -0.3555   0.02563   0.02046  -0.1135   0.9060   0.0572
  -7.250  -0.3304   0.02373   0.01830  -0.1137   0.9044   0.0577
  -7.000  -0.3008   0.02225   0.01673  -0.1144   0.9033   0.0582
  -6.750  -0.2684   0.02120   0.01561  -0.1154   0.9024   0.0586
  -6.500  -0.2612   0.02083   0.01520  -0.1112   0.8940   0.0591
  -6.250  -0.2316   0.01997   0.01426  -0.1115   0.8915   0.0596
  -6.000  -0.1991   0.01912   0.01334  -0.1122   0.8899   0.0602
  -5.750  -0.1657   0.01829   0.01243  -0.1131   0.8886   0.0609
  -5.500  -0.1308   0.01747   0.01151  -0.1143   0.8876   0.0619
  -5.250  -0.0937   0.01667   0.01060  -0.1159   0.8865   0.0626
  -5.000  -0.0834   0.01639   0.01024  -0.1120   0.8775   0.0629
  -4.750  -0.0521   0.01555   0.00931  -0.1124   0.8743   0.0636
  -4.500  -0.0154   0.01464   0.00840  -0.1139   0.8718   0.0645
  -4.250   0.0256   0.01392   0.00768  -0.1163   0.8695   0.0655
  -4.000   0.0361   0.01369   0.00743  -0.1124   0.8580   0.0660
  -3.750   0.0778   0.01305   0.00674  -0.1148   0.8530   0.0673
  -3.500   0.0951   0.01278   0.00643  -0.1122   0.8399   0.0680
  -3.250   0.1297   0.01236   0.00594  -0.1132   0.8296   0.0691
  -3.000   0.1647   0.01183   0.00535  -0.1144   0.8165   0.0705
  -2.750   0.1933   0.01149   0.00498  -0.1143   0.7986   0.0720
  -2.500   0.2226   0.01126   0.00466  -0.1142   0.7759   0.0734
  -2.250   0.2496   0.01111   0.00437  -0.1137   0.7491   0.0748
  -2.000   0.2727   0.01110   0.00417  -0.1123   0.7213   0.0763
  -1.750   0.2898   0.01102   0.00401  -0.1098   0.6964   0.0781
  -1.500   0.3070   0.01105   0.00394  -0.1073   0.6749   0.0800
  -1.250   0.3244   0.01110   0.00388  -0.1049   0.6561   0.0822
  -1.000   0.3418   0.01113   0.00383  -0.1025   0.6395   0.0853
  -0.750   0.3599   0.01117   0.00382  -0.1002   0.6248   0.0891
  -0.500   0.3789   0.01118   0.00381  -0.0981   0.6124   0.0937
  -0.250   0.3986   0.01125   0.00383  -0.0962   0.6011   0.1010
   0.000   0.4193   0.01131   0.00391  -0.0945   0.5909   0.1112
   0.250   0.4409   0.01148   0.00403  -0.0930   0.5811   0.1214
   0.500   0.4629   0.01162   0.00419  -0.0916   0.5719   0.1295
   1.000   0.5045   0.01188   0.00439  -0.0883   0.5526   0.1408
   1.250   0.5260   0.01207   0.00448  -0.0868   0.5439   0.1448
   1.500   0.5465   0.01204   0.00448  -0.0852   0.5362   0.1494
   1.750   0.5676   0.01212   0.00455  -0.0836   0.5282   0.1535
   2.000   0.5881   0.01227   0.00462  -0.0820   0.5201   0.1571
   2.250   0.6082   0.01229   0.00465  -0.0802   0.5120   0.1602
   2.500   0.6273   0.01233   0.00468  -0.0783   0.5041   0.1646
   2.750   0.6477   0.01241   0.00476  -0.0767   0.4966   0.1683
   3.000   0.6683   0.01249   0.00482  -0.0751   0.4889   0.1720
   3.250   0.6876   0.01262   0.00489  -0.0733   0.4812   0.1755
   3.500   0.7084   0.01261   0.00495  -0.0717   0.4743   0.1812
   3.750   0.7281   0.01271   0.00503  -0.0700   0.4664   0.1858
   4.000   0.7477   0.01285   0.00514  -0.0683   0.4593   0.1897
   4.250   0.7677   0.01291   0.00523  -0.0666   0.4517   0.1947
   4.500   0.7865   0.01304   0.00534  -0.0648   0.4441   0.1994
   4.750   0.8068   0.01315   0.00547  -0.0632   0.4369   0.2048
   5.000   0.8267   0.01327   0.00560  -0.0617   0.4291   0.2120
   5.250   1.0174   0.01274   0.00685  -0.0982   0.4088   1.0000
   5.500   1.0365   0.01300   0.00703  -0.0965   0.4014   1.0000
   5.750   1.0573   0.01319   0.00721  -0.0950   0.3944   1.0000
   6.000   1.0760   0.01347   0.00742  -0.0933   0.3875   1.0000
   6.250   1.0957   0.01372   0.00764  -0.0917   0.3810   1.0000
   6.500   1.1160   0.01395   0.00785  -0.0903   0.3746   1.0000
   6.750   1.1343   0.01427   0.00811  -0.0886   0.3679   1.0000
   7.000   1.1543   0.01453   0.00835  -0.0871   0.3614   1.0000
   7.250   1.1736   0.01481   0.00861  -0.0856   0.3546   1.0000
   7.500   1.1898   0.01522   0.00894  -0.0836   0.3470   1.0000
   7.750   1.2103   0.01546   0.00921  -0.0823   0.3405   1.0000
   8.000   1.2285   0.01581   0.00952  -0.0806   0.3338   1.0000
   8.250   1.2458   0.01620   0.00987  -0.0789   0.3278   1.0000
   8.500   1.2655   0.01649   0.01019  -0.0775   0.3219   1.0000
   8.750   1.2825   0.01689   0.01057  -0.0758   0.3152   1.0000
   9.000   1.2994   0.01731   0.01097  -0.0741   0.3083   1.0000
   9.250   1.3175   0.01768   0.01135  -0.0726   0.3010   1.0000
   9.500   1.3311   0.01825   0.01186  -0.0704   0.2927   1.0000
   9.750   1.3493   0.01863   0.01226  -0.0690   0.2843   1.0000
  10.000   1.3623   0.01926   0.01283  -0.0668   0.2754   1.0000
  10.250   1.3790   0.01972   0.01331  -0.0653   0.2660   1.0000
  10.500   1.3918   0.02039   0.01394  -0.0632   0.2566   1.0000
  10.750   1.4054   0.02103   0.01456  -0.0613   0.2459   1.0000
  11.000   1.4171   0.02179   0.01528  -0.0592   0.2348   1.0000
  11.250   1.4270   0.02267   0.01611  -0.0569   0.2242   1.0000
  11.500   1.4369   0.02356   0.01697  -0.0547   0.2139   1.0000
  11.750   1.4469   0.02448   0.01787  -0.0527   0.2058   1.0000
  12.000   1.4558   0.02550   0.01886  -0.0505   0.1989   1.0000
  12.250   1.4649   0.02653   0.01988  -0.0485   0.1931   1.0000
  12.500   1.4749   0.02753   0.02091  -0.0466   0.1885   1.0000
  12.750   1.4827   0.02869   0.02207  -0.0446   0.1841   1.0000
  13.000   1.4885   0.03003   0.02341  -0.0426   0.1802   1.0000
  13.250   1.5004   0.03101   0.02444  -0.0411   0.1774   1.0000
  13.500   1.5093   0.03221   0.02569  -0.0395   0.1742   1.0000
  13.750   1.5162   0.03358   0.02708  -0.0379   0.1712   1.0000
  14.000   1.5203   0.03521   0.02872  -0.0361   0.1680   1.0000
  14.250   1.5269   0.03670   0.03026  -0.0346   0.1651   1.0000
  14.500   1.5369   0.03797   0.03160  -0.0335   0.1623   1.0000
  14.750   1.5436   0.03953   0.03322  -0.0323   0.1594   1.0000
  15.000   1.5454   0.04156   0.03526  -0.0309   0.1556   1.0000
  15.250   1.5459   0.04374   0.03746  -0.0295   0.1526   1.0000
  15.500   1.5564   0.04512   0.03893  -0.0289   0.1492   1.0000
  15.750   1.5611   0.04705   0.04092  -0.0280   0.1452   1.0000
  16.000   1.5612   0.04947   0.04336  -0.0271   0.1418   1.0000
  16.250   1.5627   0.05179   0.04574  -0.0263   0.1383   1.0000
  16.500   1.5689   0.05370   0.04772  -0.0258   0.1337   1.0000
  16.750   1.5677   0.05640   0.05045  -0.0252   0.1295   1.0000
  17.000   1.5677   0.05902   0.05312  -0.0247   0.1253   1.0000
  17.250   1.5683   0.06163   0.05578  -0.0244   0.1204   1.0000
  17.500   1.5620   0.06504   0.05922  -0.0241   0.1155   1.0000
  17.750   1.5602   0.06797   0.06220  -0.0239   0.1102   1.0000
  18.000   1.5535   0.07151   0.06577  -0.0238   0.1065   1.0000
  18.250   1.5484   0.07493   0.06923  -0.0239   0.1025   1.0000
  18.500   1.5407   0.07869   0.07304  -0.0240   0.0991   1.0000
  18.750   1.5307   0.08277   0.07714  -0.0243   0.0965   1.0000
  19.000   1.5267   0.08612   0.08056  -0.0245   0.0941   1.0000
  19.250   1.5201   0.08986   0.08436  -0.0249   0.0920   1.0000
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