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GOE 289 (MVA 289) AIRFOIL (goe289-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 289 (MVA 289) AIRFOIL (goe289-il)
Reynolds number: 500,000
Max Cl/Cd: 92.08 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe289-il-500000.txt
Download as CSV file: xf-goe289-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 289 (MVA 289) 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  -0.0538   0.09399   0.09154  -0.1030   0.9439   0.0450
 -10.750  -0.1694   0.05665   0.05406  -0.1322   0.9350   0.0394
 -10.500  -0.2661   0.03234   0.02872  -0.1629   0.8957   0.0359
 -10.250  -0.2847   0.02903   0.02493  -0.1601   0.8769   0.0355
 -10.000  -0.2839   0.02716   0.02278  -0.1576   0.8621   0.0355
  -9.750  -0.2753   0.02577   0.02116  -0.1557   0.8489   0.0357
  -9.500  -0.2642   0.02443   0.01959  -0.1539   0.8365   0.0359
  -9.250  -0.2529   0.02301   0.01790  -0.1520   0.8241   0.0358
  -9.000  -0.2385   0.02184   0.01651  -0.1503   0.8123   0.0359
  -8.750  -0.2212   0.02084   0.01530  -0.1489   0.8018   0.0360
  -8.500  -0.2032   0.01992   0.01420  -0.1475   0.7909   0.0362
  -8.250  -0.1837   0.01909   0.01320  -0.1463   0.7812   0.0364
  -8.000  -0.1631   0.01836   0.01230  -0.1452   0.7720   0.0366
  -7.750  -0.1422   0.01766   0.01146  -0.1441   0.7630   0.0368
  -7.500  -0.1204   0.01704   0.01070  -0.1431   0.7545   0.0372
  -7.250  -0.0984   0.01647   0.01001  -0.1421   0.7463   0.0375
  -7.000  -0.0755   0.01602   0.00944  -0.1412   0.7384   0.0379
  -6.750  -0.0522   0.01564   0.00895  -0.1403   0.7309   0.0384
  -6.500  -0.0289   0.01525   0.00845  -0.1394   0.7230   0.0386
  -6.250  -0.0066   0.01463   0.00775  -0.1385   0.7160   0.0390
  -6.000   0.0149   0.01402   0.00712  -0.1374   0.7083   0.0396
  -5.750   0.0378   0.01362   0.00664  -0.1364   0.7010   0.0401
  -5.500   0.0608   0.01326   0.00626  -0.1355   0.6935   0.0407
  -5.250   0.0841   0.01296   0.00591  -0.1346   0.6858   0.0414
  -5.000   0.1077   0.01269   0.00558  -0.1337   0.6784   0.0421
  -4.750   0.1313   0.01243   0.00527  -0.1328   0.6703   0.0430
  -4.500   0.1554   0.01224   0.00498  -0.1320   0.6630   0.0438
  -4.250   0.1787   0.01195   0.00467  -0.1310   0.6547   0.0450
  -3.750   0.2267   0.01153   0.00417  -0.1293   0.6393   0.0489
  -3.500   0.2506   0.01136   0.00394  -0.1284   0.6316   0.0520
  -3.250   0.2747   0.01116   0.00375  -0.1276   0.6238   0.0584
  -3.000   0.2976   0.01089   0.00361  -0.1266   0.6158   0.0887
  -2.750   0.3221   0.01079   0.00356  -0.1259   0.6082   0.1134
  -2.500   0.3468   0.01075   0.00351  -0.1252   0.6004   0.1257
  -2.250   0.3717   0.01075   0.00346  -0.1246   0.5932   0.1357
  -2.000   0.3961   0.01068   0.00341  -0.1238   0.5856   0.1464
  -1.500   0.4447   0.01061   0.00330  -0.1223   0.5711   0.1662
  -1.250   0.4684   0.01057   0.00325  -0.1215   0.5640   0.1796
  -1.000   0.4923   0.01050   0.00322  -0.1207   0.5577   0.1998
  -0.750   0.5154   0.01036   0.00321  -0.1198   0.5511   0.2422
  -0.500   0.5376   0.01028   0.00327  -0.1187   0.5448   0.3094
  -0.250   0.5618   0.01025   0.00332  -0.1180   0.5384   0.3485
   0.000   0.5853   0.01027   0.00337  -0.1171   0.5319   0.3761
   0.250   0.6087   0.01033   0.00341  -0.1162   0.5259   0.3992
   0.500   0.6325   0.01032   0.00345  -0.1153   0.5199   0.4205
   0.750   0.6554   0.01035   0.00348  -0.1144   0.5140   0.4389
   1.000   0.6781   0.01038   0.00354  -0.1133   0.5085   0.4600
   1.250   0.7003   0.01031   0.00360  -0.1122   0.5028   0.4947
   1.500   0.7195   0.01020   0.00369  -0.1105   0.4972   0.5716
   1.750   0.7341   0.00997   0.00382  -0.1078   0.4919   0.7078
   2.000   0.8621   0.00990   0.00425  -0.1295   0.4815   1.0000
   2.250   0.8816   0.01009   0.00433  -0.1279   0.4759   1.0000
   2.500   0.9031   0.01018   0.00441  -0.1266   0.4705   1.0000
   2.750   0.9233   0.01031   0.00450  -0.1251   0.4648   1.0000
   3.000   0.9425   0.01052   0.00461  -0.1234   0.4594   1.0000
   3.250   0.9634   0.01063   0.00471  -0.1220   0.4541   1.0000
   3.500   0.9829   0.01078   0.00483  -0.1204   0.4485   1.0000
   3.750   0.9995   0.01099   0.00496  -0.1182   0.4430   1.0000
   4.000   1.0181   0.01111   0.00508  -0.1164   0.4378   1.0000
   4.250   1.0358   0.01127   0.00521  -0.1144   0.4320   1.0000
   4.500   1.0526   0.01150   0.00536  -0.1124   0.4268   1.0000
   4.750   1.0720   0.01167   0.00553  -0.1108   0.4219   1.0000
   5.000   1.0912   0.01185   0.00570  -0.1092   0.4167   1.0000
   5.250   1.1092   0.01209   0.00589  -0.1075   0.4119   1.0000
   5.500   1.1282   0.01234   0.00612  -0.1060   0.4072   1.0000
   5.750   1.1484   0.01253   0.00632  -0.1047   0.4027   1.0000
   6.000   1.1673   0.01278   0.00655  -0.1032   0.3980   1.0000
   6.250   1.1852   0.01311   0.00682  -0.1016   0.3935   1.0000
   6.500   1.2055   0.01334   0.00707  -0.1004   0.3896   1.0000
   6.750   1.2252   0.01359   0.00734  -0.0992   0.3854   1.0000
   7.000   1.2437   0.01390   0.00762  -0.0978   0.3812   1.0000
   7.250   1.2621   0.01428   0.00796  -0.0964   0.3772   1.0000
   7.500   1.2821   0.01457   0.00827  -0.0953   0.3739   1.0000
   7.750   1.3019   0.01485   0.00860  -0.0943   0.3707   1.0000
   8.000   1.3211   0.01519   0.00894  -0.0931   0.3673   1.0000
   8.250   1.3396   0.01557   0.00931  -0.0919   0.3641   1.0000
   8.500   1.3588   0.01602   0.00971  -0.0908   0.3603   1.0000
   8.750   1.3779   0.01635   0.01011  -0.0897   0.3578   1.0000
   9.000   1.3951   0.01672   0.01054  -0.0884   0.3537   1.0000
   9.250   1.4116   0.01717   0.01098  -0.0871   0.3493   1.0000
   9.500   1.4277   0.01772   0.01148  -0.0857   0.3448   1.0000
   9.750   1.4444   0.01816   0.01200  -0.0844   0.3410   1.0000
  10.000   1.4609   0.01864   0.01254  -0.0832   0.3370   1.0000
  10.250   1.4751   0.01924   0.01313  -0.0818   0.3322   1.0000
  10.500   1.4900   0.01989   0.01376  -0.0804   0.3281   1.0000
  10.750   1.5062   0.02043   0.01439  -0.0793   0.3246   1.0000
  11.000   1.5217   0.02103   0.01505  -0.0782   0.3208   1.0000
  11.250   1.5346   0.02179   0.01581  -0.0768   0.3163   1.0000
  11.500   1.5469   0.02262   0.01664  -0.0754   0.3119   1.0000
  11.750   1.5622   0.02329   0.01742  -0.0744   0.3081   1.0000
  12.000   1.5752   0.02412   0.01830  -0.0733   0.3037   1.0000
  12.250   1.5859   0.02511   0.01929  -0.0719   0.2994   1.0000
  12.500   1.5977   0.02607   0.02032  -0.0707   0.2948   1.0000
  12.750   1.6088   0.02712   0.02144  -0.0697   0.2886   1.0000
  13.000   1.6140   0.02860   0.02290  -0.0681   0.2823   1.0000
  13.250   1.6251   0.02975   0.02415  -0.0672   0.2749   1.0000
  13.500   1.6275   0.03159   0.02598  -0.0657   0.2655   1.0000
  13.750   1.6264   0.03380   0.02818  -0.0642   0.2518   1.0000
  14.000   1.6210   0.03646   0.03082  -0.0626   0.2323   1.0000
  14.250   1.6023   0.04042   0.03466  -0.0605   0.2065   1.0000
  14.500   1.5776   0.04510   0.03921  -0.0585   0.1801   1.0000
  14.750   1.5424   0.05109   0.04507  -0.0566   0.1504   1.0000
  15.000   1.5109   0.05700   0.05091  -0.0552   0.1257   1.0000
  15.250   1.4753   0.06370   0.05754  -0.0542   0.1009   1.0000
  15.500   1.4501   0.06945   0.06327  -0.0537   0.0868   1.0000
  15.750   1.4229   0.07568   0.06950  -0.0535   0.0723   1.0000
  16.000   1.3961   0.08202   0.07583  -0.0535   0.0558   1.0000
  16.250   1.3741   0.08791   0.08171  -0.0538   0.0439   1.0000
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