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GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il)
Reynolds number: 100,000
Max Cl/Cd: 43.42 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe223-il-100000.txt
Download as CSV file: xf-goe223-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 223 (MVA H.34) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.1341   0.10320   0.09883  -0.0837   0.9420   0.2054
  -8.750  -0.0897   0.09955   0.09510  -0.0866   0.9403   0.2155
  -8.500  -0.1613   0.08718   0.08285  -0.0947   0.9269   0.1611
  -8.250  -0.3743   0.05393   0.04844  -0.1215   0.8969   0.0889
  -8.000  -0.3389   0.04836   0.04171  -0.1296   0.8924   0.0831
  -7.750  -0.3265   0.04586   0.03900  -0.1289   0.8814   0.0824
  -7.500  -0.2820   0.04278   0.03542  -0.1336   0.8774   0.0828
  -7.250  -0.2604   0.04119   0.03349  -0.1336   0.8669   0.0835
  -7.000  -0.2154   0.03883   0.03078  -0.1371   0.8625   0.0838
  -6.750  -0.1824   0.03698   0.02877  -0.1382   0.8553   0.0843
  -6.500  -0.1484   0.03511   0.02694  -0.1393   0.8482   0.0860
  -6.250  -0.1014   0.03350   0.02535  -0.1423   0.8451   0.0898
  -6.000  -0.0787   0.03276   0.02459  -0.1413   0.8343   0.0919
  -5.750  -0.0375   0.03151   0.02334  -0.1427   0.8299   0.0946
  -5.500   0.0053   0.03027   0.02213  -0.1442   0.8270   0.0982
  -5.250   0.0244   0.02970   0.02169  -0.1429   0.8144   0.1031
  -5.000   0.0678   0.02845   0.02036  -0.1453   0.8109   0.1126
  -4.750   0.0926   0.02757   0.01948  -0.1459   0.7989   0.1245
  -4.500   0.1393   0.02565   0.01867  -0.1508   0.7949   0.3667
  -4.250   0.1601   0.02717   0.02014  -0.1481   0.7830   0.4064
  -4.000   0.1938   0.02809   0.02103  -0.1467   0.7782   0.4332
  -3.500   0.2468   0.02923   0.02206  -0.1436   0.7619   0.4631
  -3.250   0.2645   0.02993   0.02279  -0.1408   0.7514   0.4715
  -3.000   0.2949   0.03014   0.02292  -0.1400   0.7460   0.4862
  -2.750   0.3192   0.03047   0.02314  -0.1392   0.7380   0.4987
  -2.500   0.3390   0.03107   0.02381  -0.1360   0.7309   0.5086
  -2.250   0.3695   0.03115   0.02382  -0.1348   0.7273   0.5238
  -2.000   0.3880   0.03149   0.02406  -0.1345   0.7168   0.5355
  -1.750   0.4162   0.03126   0.02379  -0.1334   0.7126   0.5413
  -1.500   0.4430   0.03107   0.02350  -0.1343   0.7061   0.5451
  -1.250   0.4727   0.03084   0.02310  -0.1363   0.6993   0.5508
  -1.000   0.5072   0.03029   0.02243  -0.1377   0.6958   0.5549
  -0.750   0.5285   0.03055   0.02266  -0.1373   0.6895   0.5583
  -0.500   0.5532   0.03064   0.02268  -0.1377   0.6833   0.5624
  -0.250   0.5928   0.03007   0.02190  -0.1405   0.6799   0.5688
   0.000   0.6231   0.02987   0.02164  -0.1411   0.6762   0.5728
   0.250   0.6328   0.03090   0.02274  -0.1394   0.6682   0.5761
   0.500   0.6674   0.03055   0.02229  -0.1408   0.6646   0.5811
   0.750   0.7099   0.02986   0.02141  -0.1436   0.6619   0.5877
   1.000   0.7125   0.03132   0.02300  -0.1409   0.6534   0.5908
   1.250   0.7451   0.03100   0.02263  -0.1416   0.6492   0.5960
   1.500   0.7882   0.03019   0.02166  -0.1441   0.6462   0.6023
   1.750   0.7942   0.03162   0.02317  -0.1421   0.6387   0.6064
   2.000   0.8222   0.03156   0.02311  -0.1422   0.6339   0.6117
   2.250   0.8664   0.03060   0.02201  -0.1445   0.6306   0.6193
   2.500   0.8789   0.03163   0.02311  -0.1431   0.6241   0.6239
   2.750   0.9029   0.03177   0.02327  -0.1428   0.6183   0.6293
   3.000   0.9493   0.03067   0.02202  -0.1452   0.6146   0.6381
   3.250   0.9639   0.03142   0.02287  -0.1437   0.6085   0.6435
   3.500   0.9831   0.03200   0.02349  -0.1430   0.6026   0.6505
   3.750   1.0218   0.03144   0.02288  -0.1446   0.5992   0.6585
   4.000   1.0660   0.03066   0.02201  -0.1467   0.5964   0.6679
   4.250   1.0564   0.03289   0.02445  -0.1427   0.5878   0.6738
   4.500   1.0938   0.03226   0.02382  -0.1438   0.5837   0.6841
   4.750   1.1418   0.03117   0.02265  -0.1463   0.5805   0.6958
   5.000   1.1344   0.03317   0.02484  -0.1424   0.5719   0.7040
   5.250   1.1784   0.03203   0.02366  -0.1441   0.5668   0.7170
   5.500   1.2099   0.03177   0.02342  -0.1445   0.5614   0.7309
   5.750   1.2168   0.03281   0.02460  -0.1421   0.5541   0.7436
   6.000   1.2616   0.03175   0.02352  -0.1440   0.5494   0.7636
   6.250   1.2773   0.03235   0.02425  -0.1426   0.5435   0.7828
   6.500   1.2877   0.03305   0.02514  -0.1404   0.5370   0.8066
   6.750   1.3245   0.03207   0.02430  -0.1410   0.5327   0.8590
   7.000   1.3379   0.03279   0.02518  -0.1396   0.5264   1.0000
   7.250   1.3569   0.03358   0.02597  -0.1393   0.5194   1.0000
   7.500   1.4100   0.03276   0.02499  -0.1429   0.5147   1.0000
   7.750   1.4015   0.03462   0.02701  -0.1386   0.5068   1.0000
   8.000   1.4326   0.03458   0.02695  -0.1392   0.5007   1.0000
   8.250   1.4780   0.03404   0.02631  -0.1415   0.4955   1.0000
   8.500   1.4545   0.03616   0.02864  -0.1350   0.4865   1.0000
   8.750   1.5083   0.03514   0.02754  -0.1383   0.4811   1.0000
   9.000   1.4814   0.03736   0.02995  -0.1314   0.4721   1.0000
   9.250   1.5212   0.03662   0.02918  -0.1327   0.4654   1.0000
   9.500   1.5055   0.03846   0.03115  -0.1276   0.4563   1.0000
   9.750   1.5376   0.03789   0.03057  -0.1277   0.4488   1.0000
  10.000   1.5168   0.04019   0.03302  -0.1226   0.4389   1.0000
  10.250   1.5528   0.03935   0.03216  -0.1230   0.4319   1.0000
  10.500   1.5230   0.04248   0.03546  -0.1177   0.4210   1.0000
  10.750   1.5752   0.04036   0.03326  -0.1193   0.4144   1.0000
  11.000   1.5345   0.04459   0.03768  -0.1137   0.4027   1.0000
  11.250   1.5350   0.04613   0.03929  -0.1115   0.3931   1.0000
  11.500   1.5613   0.04534   0.03845  -0.1109   0.3837   1.0000
  11.750   1.5348   0.04943   0.04268  -0.1075   0.3725   1.0000
  12.000   1.5382   0.05092   0.04419  -0.1059   0.3625   1.0000
  12.250   1.5590   0.05068   0.04389  -0.1051   0.3524   1.0000
  12.500   1.5374   0.05498   0.04833  -0.1028   0.3421   1.0000
  12.750   1.5423   0.05661   0.04996  -0.1016   0.3324   1.0000
  13.000   1.5531   0.05765   0.05097  -0.1006   0.3231   1.0000
  13.250   1.5422   0.06131   0.05474  -0.0993   0.3139   1.0000
  13.500   1.5543   0.06225   0.05562  -0.0984   0.3044   1.0000
  13.750   1.5488   0.06540   0.05883  -0.0974   0.2951   1.0000
  14.000   1.5495   0.06786   0.06132  -0.0965   0.2860   1.0000
  14.250   1.5639   0.06856   0.06193  -0.0956   0.2769   1.0000
  14.500   1.5522   0.07278   0.06630  -0.0950   0.2688   1.0000
  14.750   1.5615   0.07413   0.06757  -0.0942   0.2592   1.0000
  15.000   1.5523   0.07812   0.07167  -0.0938   0.2508   1.0000
  15.250   1.5558   0.08034   0.07389  -0.0932   0.2422   1.0000
  15.500   1.5502   0.08388   0.07749  -0.0929   0.2334   1.0000
  15.750   1.5438   0.08763   0.08132  -0.0928   0.2249   1.0000
  16.000   1.5423   0.09069   0.08440  -0.0927   0.2166   1.0000
  16.250   1.5309   0.09539   0.08926  -0.0931   0.2090   1.0000
  16.500   1.5261   0.09904   0.09294  -0.0934   0.2007   1.0000
  16.750   1.5124   0.10433   0.09842  -0.0943   0.1936   1.0000
  17.000   1.5035   0.10885   0.10300  -0.0952   0.1852   1.0000
  17.250   1.4856   0.11509   0.10948  -0.0968   0.1773   1.0000
  17.500   1.4747   0.12019   0.11469  -0.0982   0.1690   1.0000
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