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GOE 256 (JUNKERS E) AIRFOIL (goe256-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 256 (JUNKERS E) AIRFOIL (goe256-il)
Reynolds number: 500,000
Max Cl/Cd: 92.59 at α=2.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe256-il-500000.txt
Download as CSV file: xf-goe256-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 256 (JUNKERS E) 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  -0.1679   0.09959   0.09698  -0.0855   0.9395   0.0468
 -10.750  -0.4962   0.03715   0.03338  -0.1203   0.8983   0.0404
 -10.500  -0.4995   0.03420   0.03014  -0.1183   0.8894   0.0406
 -10.250  -0.4888   0.03266   0.02846  -0.1170   0.8816   0.0409
 -10.000  -0.4743   0.03147   0.02714  -0.1159   0.8745   0.0412
  -9.750  -0.4572   0.03048   0.02604  -0.1149   0.8685   0.0415
  -9.500  -0.4441   0.02882   0.02418  -0.1136   0.8615   0.0419
  -9.250  -0.4315   0.02690   0.02200  -0.1122   0.8553   0.0424
  -9.000  -0.4172   0.02507   0.01987  -0.1108   0.8496   0.0430
  -8.750  -0.4003   0.02354   0.01809  -0.1095   0.8436   0.0438
  -8.500  -0.3818   0.02215   0.01639  -0.1084   0.8385   0.0445
  -8.250  -0.3608   0.02108   0.01502  -0.1075   0.8342   0.0451
  -8.000  -0.3401   0.01969   0.01346  -0.1067   0.8294   0.0457
  -7.750  -0.3160   0.01895   0.01269  -0.1062   0.8247   0.0463
  -7.500  -0.2908   0.01848   0.01217  -0.1059   0.8205   0.0469
  -7.250  -0.2651   0.01805   0.01164  -0.1056   0.8167   0.0477
  -7.000  -0.2399   0.01755   0.01107  -0.1052   0.8128   0.0485
  -6.750  -0.2145   0.01701   0.01045  -0.1049   0.8086   0.0495
  -6.500  -0.1887   0.01657   0.00987  -0.1045   0.8038   0.0505
  -6.250  -0.1631   0.01592   0.00907  -0.1041   0.7982   0.0516
  -6.000  -0.1380   0.01541   0.00858  -0.1036   0.7914   0.0526
  -5.750  -0.1116   0.01510   0.00823  -0.1033   0.7859   0.0537
  -5.500  -0.0844   0.01482   0.00787  -0.1032   0.7819   0.0550
  -5.250  -0.0580   0.01450   0.00751  -0.1029   0.7779   0.0564
  -5.000  -0.0311   0.01427   0.00721  -0.1026   0.7736   0.0576
  -4.750  -0.0053   0.01368   0.00662  -0.1024   0.7696   0.0594
  -4.500   0.0222   0.01352   0.00644  -0.1023   0.7657   0.0611
  -4.250   0.0493   0.01335   0.00624  -0.1021   0.7618   0.0631
  -4.000   0.0764   0.01319   0.00604  -0.1019   0.7575   0.0649
  -3.750   0.1021   0.01270   0.00556  -0.1016   0.7533   0.0671
  -3.500   0.1294   0.01251   0.00536  -0.1014   0.7492   0.0692
  -3.250   0.1569   0.01239   0.00520  -0.1013   0.7452   0.0717
  -3.000   0.1840   0.01231   0.00510  -0.1011   0.7408   0.0738
  -2.750   0.2092   0.01186   0.00469  -0.1007   0.7362   0.0770
  -2.500   0.2365   0.01171   0.00452  -0.1005   0.7320   0.0797
  -2.250   0.2641   0.01162   0.00439  -0.1004   0.7277   0.0826
  -2.000   0.2896   0.01135   0.00415  -0.0999   0.7227   0.0858
  -1.750   0.3159   0.01115   0.00397  -0.0996   0.7177   0.0893
  -1.500   0.3433   0.01105   0.00383  -0.0995   0.7131   0.0930
  -1.250   0.3699   0.01091   0.00369  -0.0992   0.7082   0.0968
  -1.000   0.3957   0.01072   0.00355  -0.0988   0.7024   0.1020
  -0.750   0.4227   0.01063   0.00343  -0.0985   0.6967   0.1071
  -0.500   0.4490   0.01048   0.00331  -0.0982   0.6910   0.1152
  -0.250   0.4748   0.01033   0.00322  -0.0978   0.6844   0.1279
   0.000   0.4997   0.01002   0.00311  -0.0973   0.6782   0.1845
   0.250   0.5188   0.00924   0.00311  -0.0959   0.6715   0.4243
   0.500   0.5327   0.00839   0.00309  -0.0932   0.6638   0.6730
   0.750   0.5568   0.00817   0.00355  -0.0912   0.6560   0.9318
   1.000   0.5883   0.00837   0.00372  -0.0915   0.6456   0.9558
   1.250   0.6407   0.00863   0.00390  -0.0965   0.6337   0.9695
   1.500   0.6980   0.00885   0.00403  -0.1027   0.6192   0.9804
   1.750   0.7635   0.00900   0.00405  -0.1108   0.5996   0.9881
   2.000   0.8288   0.00914   0.00401  -0.1190   0.5755   0.9976
   2.250   0.8629   0.00932   0.00404  -0.1206   0.5534   1.0000
   2.500   0.8831   0.00955   0.00414  -0.1192   0.5344   1.0000
   2.750   0.9029   0.00978   0.00426  -0.1177   0.5181   1.0000
   3.000   0.9224   0.01003   0.00440  -0.1162   0.5042   1.0000
   3.250   0.9420   0.01025   0.00455  -0.1147   0.4919   1.0000
   3.500   0.9619   0.01045   0.00469  -0.1133   0.4816   1.0000
   4.000   1.0000   0.01087   0.00501  -0.1100   0.4636   1.0000
   4.250   1.0174   0.01112   0.00519  -0.1081   0.4557   1.0000
   4.500   1.0361   0.01129   0.00535  -0.1064   0.4486   1.0000
   4.750   1.0526   0.01152   0.00553  -0.1043   0.4407   1.0000
   5.000   1.0684   0.01173   0.00571  -0.1020   0.4329   1.0000
   5.250   1.0833   0.01193   0.00588  -0.0996   0.4250   1.0000
   5.500   1.0959   0.01220   0.00609  -0.0967   0.4187   1.0000
   5.750   1.1111   0.01234   0.00626  -0.0943   0.4134   1.0000
   6.000   1.1220   0.01253   0.00644  -0.0910   0.4079   1.0000
   6.250   1.1258   0.01276   0.00662  -0.0863   0.4028   1.0000
   6.500   1.1348   0.01289   0.00678  -0.0827   0.3984   1.0000
   6.750   1.1451   0.01305   0.00696  -0.0794   0.3939   1.0000
   7.000   1.1560   0.01328   0.00717  -0.0762   0.3895   1.0000
   7.250   1.1678   0.01360   0.00744  -0.0734   0.3848   1.0000
   7.500   1.1845   0.01378   0.00768  -0.0715   0.3804   1.0000
   7.750   1.2014   0.01404   0.00795  -0.0698   0.3752   1.0000
   8.000   1.2178   0.01439   0.00827  -0.0680   0.3704   1.0000
   8.250   1.2362   0.01472   0.00861  -0.0667   0.3663   1.0000
   8.500   1.2560   0.01499   0.00894  -0.0656   0.3620   1.0000
   8.750   1.2743   0.01534   0.00930  -0.0643   0.3570   1.0000
   9.000   1.2916   0.01578   0.00971  -0.0630   0.3523   1.0000
   9.250   1.3109   0.01614   0.01011  -0.0619   0.3481   1.0000
   9.500   1.3302   0.01650   0.01053  -0.0610   0.3432   1.0000
   9.750   1.3476   0.01696   0.01099  -0.0597   0.3382   1.0000
  10.000   1.3644   0.01748   0.01151  -0.0585   0.3332   1.0000
  10.250   1.3832   0.01789   0.01200  -0.0576   0.3270   1.0000
  10.500   1.3975   0.01853   0.01261  -0.0561   0.3197   1.0000
  10.750   1.4147   0.01907   0.01320  -0.0550   0.3123   1.0000
  11.000   1.4291   0.01976   0.01389  -0.0537   0.3044   1.0000
  11.250   1.4449   0.02041   0.01457  -0.0526   0.2963   1.0000
  11.500   1.4574   0.02126   0.01541  -0.0511   0.2870   1.0000
  11.750   1.4713   0.02205   0.01623  -0.0499   0.2756   1.0000
  12.000   1.4819   0.02308   0.01722  -0.0484   0.2617   1.0000
  12.250   1.4894   0.02433   0.01843  -0.0467   0.2445   1.0000
  12.500   1.4921   0.02596   0.01996  -0.0446   0.2233   1.0000
  12.750   1.4906   0.02793   0.02180  -0.0423   0.1984   1.0000
  13.000   1.4882   0.03008   0.02384  -0.0400   0.1803   1.0000
  13.250   1.4881   0.03212   0.02582  -0.0381   0.1681   1.0000
  13.500   1.4922   0.03390   0.02760  -0.0367   0.1597   1.0000
  13.750   1.4939   0.03592   0.02962  -0.0352   0.1529   1.0000
  14.000   1.5011   0.03755   0.03129  -0.0341   0.1476   1.0000
  14.250   1.5042   0.03954   0.03331  -0.0329   0.1426   1.0000
  14.500   1.5085   0.04149   0.03529  -0.0319   0.1382   1.0000
  14.750   1.5151   0.04328   0.03713  -0.0311   0.1336   1.0000
  15.000   1.5171   0.04553   0.03942  -0.0301   0.1290   1.0000
  15.250   1.5204   0.04769   0.04163  -0.0293   0.1248   1.0000
  15.500   1.5257   0.04971   0.04370  -0.0287   0.1203   1.0000
  15.750   1.5255   0.05233   0.04634  -0.0279   0.1157   1.0000
  16.000   1.5285   0.05467   0.04874  -0.0274   0.1108   1.0000
  16.250   1.5288   0.05737   0.05148  -0.0269   0.1053   1.0000
  16.500   1.5271   0.06031   0.05447  -0.0265   0.0995   1.0000
  16.750   1.5205   0.06389   0.05804  -0.0262   0.0912   1.0000
  17.000   1.5125   0.06773   0.06188  -0.0260   0.0795   1.0000
  17.250   1.4944   0.07286   0.06694  -0.0259   0.0631   1.0000
  17.500   1.4694   0.07896   0.07296  -0.0260   0.0471   1.0000
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