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GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il)
Reynolds number: 50,000
Max Cl/Cd: 38.78 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe239-il-50000-n5.txt
Download as CSV file: xf-goe239-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 239 (MVA H.31) AIRFOIL                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3036   0.10845   0.10215  -0.0262   1.0000   0.1330
  -7.500  -0.3150   0.10720   0.10101  -0.0239   1.0000   0.1345
  -7.250  -0.3291   0.10611   0.10002  -0.0216   1.0000   0.1357
  -7.000  -0.3282   0.10365   0.09762  -0.0307   0.9910   0.1395
  -6.750  -0.3071   0.09452   0.08838  -0.0367   0.9850   0.0980
  -6.250  -0.2611   0.07999   0.07362  -0.0596   0.9656   0.0809
  -6.000  -0.2359   0.07534   0.06890  -0.0649   0.9578   0.0803
  -5.750  -0.1991   0.06740   0.06075  -0.0785   0.9497   0.0810
  -5.500  -0.1647   0.06004   0.05311  -0.0890   0.9408   0.0811
  -5.250  -0.1199   0.05276   0.04540  -0.1003   0.9347   0.0809
  -5.000  -0.0848   0.04826   0.04062  -0.1064   0.9258   0.0823
  -4.750  -0.0454   0.04596   0.03821  -0.1107   0.9195   0.0858
  -4.500  -0.0029   0.04127   0.03294  -0.1179   0.9108   0.0879
  -4.250   0.0471   0.03706   0.02798  -0.1251   0.9050   0.0900
  -4.000   0.0905   0.03429   0.02446  -0.1297   0.8971   0.0942
  -3.750   0.1311   0.03255   0.02251  -0.1328   0.8895   0.0990
  -3.500   0.1693   0.03108   0.02075  -0.1351   0.8809   0.1033
  -3.250   0.2091   0.02968   0.01892  -0.1374   0.8727   0.1090
  -3.000   0.2417   0.02877   0.01800  -0.1384   0.8619   0.1170
  -2.750   0.2819   0.02768   0.01672  -0.1405   0.8544   0.1273
  -2.500   0.3122   0.02709   0.01610  -0.1409   0.8420   0.1406
  -2.250   0.3450   0.02662   0.01569  -0.1417   0.8308   0.1599
  -2.000   0.3823   0.02609   0.01515  -0.1430   0.8220   0.1983
  -1.750   0.4113   0.02593   0.01506  -0.1430   0.8088   0.2477
  -1.500   0.4403   0.02597   0.01511  -0.1429   0.7965   0.2967
  -1.250   0.4718   0.02594   0.01504  -0.1432   0.7865   0.3371
  -1.000   0.5011   0.02589   0.01490  -0.1431   0.7751   0.3706
  -0.750   0.5279   0.02588   0.01484  -0.1427   0.7629   0.4035
  -0.500   0.5573   0.02568   0.01460  -0.1427   0.7528   0.4327
  -0.250   0.5876   0.02545   0.01428  -0.1428   0.7431   0.4549
   0.000   0.6145   0.02539   0.01416  -0.1425   0.7318   0.4712
   0.250   0.6452   0.02514   0.01386  -0.1427   0.7234   0.4895
   0.500   0.6721   0.02505   0.01382  -0.1424   0.7131   0.5113
   0.750   0.6993   0.02496   0.01381  -0.1421   0.7035   0.5412
   1.000   0.7279   0.02462   0.01365  -0.1418   0.6954   0.5919
   1.500   0.7780   0.02405   0.01339  -0.1397   0.6780   1.0000
   1.750   0.8033   0.02451   0.01368  -0.1394   0.6675   1.0000
   2.000   0.8329   0.02471   0.01368  -0.1394   0.6593   1.0000
   2.250   0.8602   0.02504   0.01386  -0.1392   0.6500   1.0000
   2.500   0.8872   0.02538   0.01409  -0.1389   0.6411   1.0000
   2.750   0.9160   0.02562   0.01420  -0.1388   0.6326   1.0000
   3.000   0.9410   0.02609   0.01462  -0.1383   0.6232   1.0000
   3.250   0.9711   0.02627   0.01468  -0.1383   0.6153   1.0000
   3.500   0.9941   0.02685   0.01525  -0.1376   0.6053   1.0000
   3.750   1.0244   0.02704   0.01533  -0.1376   0.5977   1.0000
   4.000   1.0463   0.02769   0.01602  -0.1368   0.5876   1.0000
   4.250   1.0739   0.02806   0.01633  -0.1365   0.5793   1.0000
   4.500   1.0976   0.02863   0.01694  -0.1359   0.5698   1.0000
   4.750   1.1227   0.02915   0.01746  -0.1354   0.5612   1.0000
   5.000   1.1476   0.02968   0.01802  -0.1348   0.5523   1.0000
   5.250   1.1704   0.03034   0.01874  -0.1341   0.5432   1.0000
   5.500   1.1961   0.03084   0.01927  -0.1336   0.5347   1.0000
   5.750   1.2166   0.03165   0.02018  -0.1326   0.5254   1.0000
   6.000   1.2428   0.03214   0.02070  -0.1322   0.5172   1.0000
   6.250   1.2607   0.03310   0.02182  -0.1309   0.5078   1.0000
   6.500   1.2872   0.03359   0.02235  -0.1305   0.5000   1.0000
   6.750   1.3022   0.03470   0.02364  -0.1289   0.4902   1.0000
   7.000   1.3291   0.03515   0.02416  -0.1286   0.4827   1.0000
   7.250   1.3405   0.03646   0.02569  -0.1266   0.4728   1.0000
   7.500   1.3676   0.03691   0.02620  -0.1263   0.4659   1.0000
   7.750   1.3752   0.03848   0.02801  -0.1240   0.4563   1.0000
   8.000   1.4020   0.03890   0.02854  -0.1236   0.4496   1.0000
   8.250   1.4056   0.04068   0.03057  -0.1209   0.4401   1.0000
   8.500   1.4321   0.04108   0.03107  -0.1204   0.4337   1.0000
   8.750   1.4306   0.04323   0.03348  -0.1173   0.4249   1.0000
   9.000   1.4544   0.04378   0.03417  -0.1165   0.4187   1.0000
   9.250   1.4488   0.04608   0.03672  -0.1131   0.4098   1.0000
   9.500   1.4813   0.04554   0.03627  -0.1127   0.4020   1.0000
   9.750   1.4592   0.04861   0.03955  -0.1077   0.3925   1.0000
  10.000   1.4719   0.04905   0.04011  -0.1055   0.3828   1.0000
  10.250   1.4948   0.04830   0.03940  -0.1037   0.3711   1.0000
  10.500   1.4730   0.05162   0.04292  -0.0997   0.3609   1.0000
  10.750   1.4719   0.05329   0.04474  -0.0971   0.3502   1.0000
  11.000   1.4877   0.05337   0.04489  -0.0953   0.3393   1.0000
  11.250   1.4759   0.05649   0.04819  -0.0930   0.3294   1.0000
  11.500   1.4666   0.05960   0.05144  -0.0911   0.3195   1.0000
  11.750   1.4754   0.06053   0.05246  -0.0894   0.3082   1.0000
  12.000   1.4685   0.06352   0.05560  -0.0880   0.2973   1.0000
  12.250   1.4480   0.06868   0.06094  -0.0873   0.2874   1.0000
  12.500   1.4494   0.07085   0.06323  -0.0862   0.2761   1.0000
  12.750   1.4537   0.07253   0.06501  -0.0850   0.2635   1.0000
  13.000   1.4227   0.08003   0.07271  -0.0860   0.2531   1.0000
  13.250   1.4106   0.08464   0.07749  -0.0862   0.2405   1.0000
  13.500   1.4034   0.08850   0.08145  -0.0862   0.2268   1.0000
  13.750   1.3950   0.09267   0.08572  -0.0865   0.2121   1.0000
  14.000   1.3840   0.09744   0.09059  -0.0872   0.1964   1.0000
  14.250   1.3736   0.10225   0.09546  -0.0881   0.1797   1.0000
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