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GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il)
Reynolds number: 100,000
Max Cl/Cd: 54.52 at α=9.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe239-il-100000.txt
Download as CSV file: xf-goe239-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.500  -0.3270   0.10367   0.09934  -0.0211   1.0000   0.1069
  -7.250  -0.3421   0.10278   0.09853  -0.0185   1.0000   0.1089
  -7.000  -0.3626   0.10227   0.09812  -0.0165   1.0000   0.1109
  -6.500  -0.3616   0.09610   0.09205  -0.0233   0.9955   0.1153
  -6.250  -0.3329   0.09256   0.08848  -0.0237   0.9906   0.1208
  -6.000  -0.2995   0.08691   0.08279  -0.0398   0.9799   0.1302
  -5.750  -0.2530   0.08256   0.07831  -0.0554   0.9713   0.1432
  -5.500  -0.2360   0.07840   0.07419  -0.0529   0.9635   0.1455
  -5.250  -0.1928   0.07389   0.06958  -0.0651   0.9545   0.1592
  -5.000  -0.1695   0.07127   0.06698  -0.0617   0.9473   0.1648
  -4.750  -0.1303   0.06699   0.06262  -0.0707   0.9377   0.1771
  -4.500  -0.0828   0.06266   0.05817  -0.0806   0.9304   0.1916
  -4.250   0.0317   0.03843   0.03245  -0.1227   0.9288   0.1158
  -4.000   0.0792   0.03311   0.02642  -0.1292   0.9194   0.1085
  -3.750   0.1373   0.02947   0.02200  -0.1362   0.9151   0.1103
  -3.500   0.1834   0.02727   0.01923  -0.1398   0.9060   0.1119
  -3.250   0.2359   0.02506   0.01668  -0.1444   0.9004   0.1157
  -3.000   0.2793   0.02377   0.01530  -0.1470   0.8917   0.1241
  -2.750   0.3240   0.02233   0.01374  -0.1497   0.8836   0.1324
  -2.500   0.3611   0.02138   0.01281  -0.1508   0.8718   0.1461
  -2.250   0.4052   0.02041   0.01191  -0.1530   0.8646   0.1718
  -2.000   0.4371   0.01994   0.01161  -0.1531   0.8503   0.2158
  -1.750   0.4679   0.01980   0.01170  -0.1530   0.8363   0.2956
  -1.500   0.4974   0.01993   0.01181  -0.1525   0.8229   0.3447
  -1.250   0.5277   0.01983   0.01165  -0.1522   0.8109   0.3771
  -1.000   0.5586   0.01957   0.01130  -0.1522   0.8001   0.4039
  -0.750   0.5849   0.01943   0.01115  -0.1515   0.7867   0.4263
  -0.500   0.6126   0.01928   0.01093  -0.1512   0.7746   0.4479
  -0.250   0.6421   0.01895   0.01060  -0.1510   0.7651   0.4692
   0.000   0.6697   0.01875   0.01041  -0.1507   0.7540   0.4899
   0.250   0.6965   0.01863   0.01029  -0.1503   0.7429   0.5087
   0.500   0.7268   0.01836   0.00995  -0.1502   0.7345   0.5306
   0.750   0.7530   0.01825   0.00994  -0.1497   0.7236   0.5581
   1.000   0.7799   0.01806   0.00990  -0.1492   0.7140   0.6035
   1.250   0.8009   0.01707   0.00960  -0.1468   0.7056   1.0000
   1.500   0.8298   0.01737   0.00965  -0.1471   0.6953   1.0000
   1.750   0.8604   0.01748   0.00951  -0.1472   0.6872   1.0000
   2.000   0.8869   0.01779   0.00971  -0.1469   0.6768   1.0000
   2.250   0.9148   0.01804   0.00983  -0.1467   0.6678   1.0000
   2.500   0.9430   0.01826   0.00992  -0.1465   0.6587   1.0000
   2.750   0.9691   0.01863   0.01024  -0.1461   0.6491   1.0000
   3.000   0.9986   0.01885   0.01030  -0.1461   0.6412   1.0000
   3.250   1.0232   0.01930   0.01076  -0.1455   0.6310   1.0000
   3.500   1.0518   0.01960   0.01096  -0.1454   0.6229   1.0000
   3.750   1.0769   0.02004   0.01140  -0.1449   0.6131   1.0000
   4.000   1.1035   0.02047   0.01179  -0.1446   0.6043   1.0000
   4.250   1.1302   0.02088   0.01218  -0.1442   0.5952   1.0000
   4.500   1.1550   0.02141   0.01273  -0.1437   0.5856   1.0000
   4.750   1.1835   0.02178   0.01301  -0.1436   0.5770   1.0000
   5.000   1.2061   0.02238   0.01371  -0.1427   0.5661   1.0000
   5.250   1.2330   0.02286   0.01415  -0.1424   0.5571   1.0000
   5.500   1.2574   0.02340   0.01474  -0.1418   0.5469   1.0000
   5.750   1.2810   0.02405   0.01547  -0.1411   0.5370   1.0000
   6.000   1.3085   0.02453   0.01590  -0.1409   0.5281   1.0000
   6.250   1.3293   0.02526   0.01678  -0.1398   0.5171   1.0000
   6.500   1.3564   0.02577   0.01727  -0.1395   0.5084   1.0000
   6.750   1.3779   0.02643   0.01805  -0.1385   0.4977   1.0000
   7.000   1.4004   0.02714   0.01886  -0.1376   0.4883   1.0000
   7.250   1.4262   0.02755   0.01929  -0.1371   0.4791   1.0000
   7.500   1.4453   0.02818   0.02008  -0.1357   0.4678   1.0000
   7.750   1.4700   0.02837   0.02028  -0.1349   0.4576   1.0000
   8.000   1.4937   0.02842   0.02035  -0.1339   0.4464   1.0000
   8.250   1.5117   0.02884   0.02095  -0.1322   0.4350   1.0000
   8.500   1.5344   0.02904   0.02121  -0.1312   0.4252   1.0000
   8.750   1.5575   0.02904   0.02124  -0.1301   0.4148   1.0000
   9.000   1.5736   0.02944   0.02182  -0.1281   0.4034   1.0000
   9.250   1.5933   0.02966   0.02215  -0.1266   0.3930   1.0000
   9.500   1.6155   0.02963   0.02211  -0.1254   0.3822   1.0000
   9.750   1.6292   0.03001   0.02265  -0.1230   0.3701   1.0000
  10.000   1.6423   0.03043   0.02322  -0.1206   0.3579   1.0000
  10.250   1.6532   0.03076   0.02365  -0.1178   0.3438   1.0000
  10.500   1.6599   0.03118   0.02414  -0.1145   0.3283   1.0000
  10.750   1.6617   0.03180   0.02483  -0.1105   0.3121   1.0000
  11.000   1.6577   0.03264   0.02575  -0.1057   0.2960   1.0000
  11.250   1.6517   0.03383   0.02697  -0.1012   0.2781   1.0000
  11.500   1.6421   0.03551   0.02872  -0.0969   0.2574   1.0000
  11.750   1.6280   0.03784   0.03108  -0.0929   0.2323   1.0000
  12.000   1.6091   0.04106   0.03424  -0.0894   0.2018   1.0000
  12.250   1.5875   0.04512   0.03818  -0.0866   0.1678   1.0000
  12.500   1.5643   0.04980   0.04264  -0.0845   0.1463   1.0000
  12.750   1.5425   0.05474   0.04743  -0.0830   0.1326   1.0000
  13.000   1.5234   0.05965   0.05228  -0.0819   0.1220   1.0000
  13.250   1.5082   0.06434   0.05695  -0.0811   0.1125   1.0000
  13.500   1.4950   0.06879   0.06134  -0.0803   0.1047   1.0000
  13.750   1.4860   0.07291   0.06548  -0.0797   0.0968   1.0000
  14.000   1.4807   0.07651   0.06908  -0.0789   0.0895   1.0000
  14.250   1.4771   0.07983   0.07231  -0.0781   0.0831   1.0000
  14.500   1.4769   0.08291   0.07549  -0.0773   0.0772   1.0000
  14.750   1.4851   0.08438   0.07674  -0.0753   0.0716   1.0000
  15.000   1.4895   0.08699   0.07952  -0.0742   0.0675   1.0000
  15.250   1.4960   0.08917   0.08170  -0.0732   0.0636   1.0000
  15.500   1.5150   0.08979   0.08224  -0.0703   0.0596   1.0000
  15.750   1.5181   0.09290   0.08561  -0.0698   0.0577   1.0000
  16.000   1.5217   0.09596   0.08886  -0.0692   0.0557   1.0000
  16.250   1.5257   0.09892   0.09193  -0.0689   0.0538   1.0000
  16.500   1.5492   0.10037   0.09326  -0.0664   0.0509   1.0000
  16.750   1.5350   0.10546   0.09867  -0.0677   0.0504   1.0000
  17.000   1.5210   0.11087   0.10438  -0.0695   0.0501   1.0000
  17.250   1.5063   0.11667   0.11048  -0.0716   0.0498   1.0000
  17.500   1.4902   0.12294   0.11703  -0.0744   0.0496   1.0000
  17.750   1.4722   0.12978   0.12414  -0.0778   0.0496   1.0000
  18.000   1.4522   0.13726   0.13189  -0.0821   0.0497   1.0000
  18.250   1.4307   0.14547   0.14035  -0.0871   0.0498   1.0000
  18.500   1.4078   0.15450   0.14960  -0.0931   0.0501   1.0000
  18.750   1.3842   0.16435   0.15966  -0.0999   0.0505   1.0000
  19.000   1.3617   0.17477   0.17022  -0.1070   0.0510   1.0000
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