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GOE 239 (MVA H.31) AIRFOIL (goe239-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 239 (MVA H.31) AIRFOIL (goe239-il)
Reynolds number: 200,000
Max Cl/Cd: 83.64 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe239-il-200000-n5.txt
Download as CSV file: xf-goe239-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2746   0.11754   0.11387  -0.0411   1.0000   0.0253
 -10.500  -0.2755   0.11465   0.11102  -0.0411   1.0000   0.0253
 -10.250  -0.2788   0.11204   0.10846  -0.0405   1.0000   0.0254
 -10.000  -0.2689   0.10750   0.10392  -0.0443   0.9963   0.0257
  -9.750  -0.2665   0.10085   0.09727  -0.0505   0.9907   0.0270
  -9.500  -0.2497   0.09798   0.09441  -0.0533   0.9862   0.0279
  -9.250  -0.2350   0.09468   0.09110  -0.0563   0.9801   0.0284
  -8.750  -0.2123   0.08653   0.08294  -0.0640   0.9650   0.0293
  -8.500  -0.2017   0.08233   0.07873  -0.0682   0.9561   0.0305
  -8.250  -0.1954   0.07665   0.07303  -0.0740   0.9460   0.0316
  -7.750  -0.1831   0.06005   0.05636  -0.0943   0.9235   0.0332
  -7.500  -0.1582   0.05885   0.05511  -0.0968   0.9167   0.0340
  -7.250  -0.1285   0.02980   0.02488  -0.1392   0.9045   0.0364
  -7.000  -0.0984   0.02582   0.02022  -0.1437   0.8984   0.0382
  -6.750  -0.0688   0.02340   0.01720  -0.1460   0.8920   0.0394
  -6.500  -0.0391   0.02166   0.01519  -0.1474   0.8867   0.0402
  -6.250  -0.0118   0.02064   0.01403  -0.1478   0.8794   0.0410
  -6.000   0.0170   0.01985   0.01310  -0.1484   0.8729   0.0421
  -5.750   0.0456   0.01908   0.01215  -0.1488   0.8665   0.0436
  -5.500   0.0740   0.01825   0.01111  -0.1491   0.8591   0.0448
  -5.250   0.1033   0.01742   0.01007  -0.1494   0.8529   0.0458
  -5.000   0.1312   0.01674   0.00923  -0.1495   0.8444   0.0468
  -4.750   0.1602   0.01610   0.00843  -0.1496   0.8369   0.0478
  -4.500   0.1879   0.01547   0.00778  -0.1497   0.8271   0.0494
  -4.250   0.2162   0.01507   0.00732  -0.1497   0.8178   0.0514
  -4.000   0.2445   0.01466   0.00683  -0.1497   0.8076   0.0533
  -3.750   0.2728   0.01426   0.00635  -0.1497   0.7965   0.0552
  -3.500   0.3012   0.01392   0.00590  -0.1496   0.7845   0.0571
  -3.250   0.3295   0.01352   0.00547  -0.1496   0.7705   0.0600
  -3.000   0.3577   0.01328   0.00516  -0.1495   0.7539   0.0640
  -2.750   0.3858   0.01307   0.00484  -0.1494   0.7349   0.0692
  -2.500   0.4138   0.01285   0.00454  -0.1493   0.7138   0.0762
  -2.250   0.4416   0.01269   0.00425  -0.1491   0.6909   0.0849
  -2.000   0.4691   0.01258   0.00399  -0.1489   0.6676   0.0976
  -1.750   0.4965   0.01243   0.00377  -0.1487   0.6475   0.1197
  -1.250   0.5511   0.01235   0.00378  -0.1485   0.6166   0.2268
  -1.000   0.5785   0.01244   0.00381  -0.1483   0.6047   0.2514
  -0.750   0.6059   0.01255   0.00386  -0.1481   0.5950   0.2695
  -0.500   0.6334   0.01266   0.00392  -0.1480   0.5858   0.2863
  -0.250   0.6609   0.01278   0.00399  -0.1478   0.5778   0.3014
   0.000   0.6885   0.01290   0.00404  -0.1477   0.5698   0.3143
   0.250   0.7160   0.01302   0.00413  -0.1476   0.5628   0.3266
   0.500   0.7435   0.01313   0.00422  -0.1474   0.5556   0.3399
   0.750   0.7709   0.01327   0.00431  -0.1473   0.5493   0.3533
   1.000   0.7985   0.01335   0.00440  -0.1472   0.5424   0.3669
   1.250   0.8257   0.01347   0.00450  -0.1470   0.5355   0.3803
   1.500   0.8530   0.01359   0.00460  -0.1469   0.5293   0.3934
   1.750   0.8802   0.01366   0.00471  -0.1467   0.5227   0.4074
   2.000   0.9072   0.01378   0.00484  -0.1466   0.5171   0.4233
   2.250   0.9346   0.01385   0.00498  -0.1465   0.5120   0.4430
   2.500   0.9617   0.01388   0.00514  -0.1463   0.5065   0.4734
   2.750   0.9876   0.01370   0.00535  -0.1460   0.5017   0.6240
   3.000   1.0077   0.01329   0.00540  -0.1440   0.4974   1.0000
   3.250   1.0349   0.01345   0.00557  -0.1438   0.4918   1.0000
   3.500   1.0618   0.01365   0.00575  -0.1436   0.4860   1.0000
   3.750   1.0885   0.01389   0.00593  -0.1434   0.4808   1.0000
   4.000   1.1152   0.01405   0.00614  -0.1432   0.4744   1.0000
   4.250   1.1416   0.01426   0.00635  -0.1429   0.4685   1.0000
   4.500   1.1679   0.01449   0.00656  -0.1426   0.4630   1.0000
   4.750   1.1941   0.01467   0.00680  -0.1423   0.4563   1.0000
   5.000   1.2198   0.01491   0.00703  -0.1419   0.4501   1.0000
   5.250   1.2456   0.01511   0.00729  -0.1416   0.4430   1.0000
   5.500   1.2709   0.01534   0.00754  -0.1411   0.4356   1.0000
   5.750   1.2957   0.01556   0.00781  -0.1406   0.4263   1.0000
   6.000   1.3195   0.01579   0.00804  -0.1399   0.4147   1.0000
   6.250   1.3425   0.01605   0.00829  -0.1390   0.4008   1.0000
   6.500   1.3651   0.01635   0.00859  -0.1382   0.3868   1.0000
   6.750   1.3875   0.01668   0.00892  -0.1373   0.3734   1.0000
   7.000   1.4098   0.01704   0.00929  -0.1363   0.3616   1.0000
   7.250   1.4312   0.01745   0.00969  -0.1353   0.3503   1.0000
   7.500   1.4517   0.01790   0.01014  -0.1341   0.3389   1.0000
   7.750   1.4715   0.01838   0.01061  -0.1329   0.3271   1.0000
   8.000   1.4906   0.01889   0.01112  -0.1315   0.3142   1.0000
   8.250   1.5092   0.01942   0.01166  -0.1301   0.3025   1.0000
   8.500   1.5271   0.01999   0.01225  -0.1286   0.2933   1.0000
   8.750   1.5454   0.02051   0.01284  -0.1271   0.2844   1.0000
   9.000   1.5620   0.02109   0.01346  -0.1254   0.2761   1.0000
   9.250   1.5750   0.02173   0.01413  -0.1230   0.2655   1.0000
   9.500   1.5874   0.02244   0.01487  -0.1207   0.2524   1.0000
   9.750   1.5969   0.02332   0.01574  -0.1181   0.2361   1.0000
  10.000   1.6054   0.02431   0.01670  -0.1155   0.2191   1.0000
  10.250   1.6124   0.02545   0.01781  -0.1129   0.2000   1.0000
  10.500   1.6160   0.02688   0.01915  -0.1100   0.1700   1.0000
  10.750   1.6084   0.02920   0.02121  -0.1063   0.1308   1.0000
  11.000   1.6033   0.03154   0.02343  -0.1032   0.1099   1.0000
  11.250   1.6016   0.03373   0.02562  -0.1007   0.0942   1.0000
  11.500   1.6002   0.03601   0.02789  -0.0985   0.0784   1.0000
  11.750   1.5971   0.03853   0.03041  -0.0964   0.0683   1.0000
  12.000   1.5950   0.04110   0.03301  -0.0946   0.0626   1.0000
  12.250   1.5923   0.04383   0.03581  -0.0931   0.0583   1.0000
  12.500   1.5912   0.04651   0.03860  -0.0918   0.0548   1.0000
  12.750   1.5872   0.04962   0.04181  -0.0907   0.0517   1.0000
  13.000   1.5804   0.05320   0.04548  -0.0898   0.0490   1.0000
  13.250   1.5798   0.05619   0.04863  -0.0893   0.0463   1.0000
  13.500   1.5768   0.05959   0.05217  -0.0889   0.0433   1.0000
  13.750   1.5701   0.06360   0.05628  -0.0888   0.0407   1.0000
  14.000   1.5661   0.06736   0.06016  -0.0887   0.0380   1.0000
  14.250   1.5621   0.07115   0.06407  -0.0888   0.0350   1.0000
  14.500   1.5546   0.07552   0.06852  -0.0891   0.0327   1.0000
  14.750   1.5502   0.07949   0.07261  -0.0894   0.0302   1.0000
  15.000   1.5435   0.08382   0.07704  -0.0899   0.0281   1.0000
  15.250   1.5352   0.08843   0.08171  -0.0905   0.0266   1.0000
  15.500   1.5286   0.09284   0.08626  -0.0911   0.0251   1.0000
  15.750   1.5215   0.09740   0.09092  -0.0918   0.0237   1.0000
  16.000   1.5136   0.10212   0.09573  -0.0928   0.0226   1.0000
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