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GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il)
Reynolds number: 100,000
Max Cl/Cd: 48.95 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe223-il-100000-n5.txt
Download as CSV file: xf-goe223-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1842   0.09995   0.09493  -0.0965   0.9584   0.0425
 -11.750  -0.2091   0.08855   0.08351  -0.1032   0.9515   0.0421
 -11.500  -0.2550   0.07460   0.06939  -0.1143   0.9448   0.0411
 -11.250  -0.2918   0.06563   0.06020  -0.1221   0.9338   0.0405
 -11.000  -0.3157   0.05934   0.05366  -0.1279   0.9235   0.0403
 -10.750  -0.3312   0.05449   0.04855  -0.1323   0.9132   0.0404
 -10.500  -0.3466   0.05119   0.04503  -0.1342   0.9008   0.0405
 -10.250  -0.3501   0.04781   0.04136  -0.1375   0.8912   0.0407
 -10.000  -0.3447   0.04486   0.03807  -0.1395   0.8830   0.0411
  -9.750  -0.3365   0.04246   0.03536  -0.1403   0.8746   0.0416
  -9.500  -0.3225   0.04022   0.03277  -0.1414   0.8678   0.0427
  -9.250  -0.3045   0.03819   0.03033  -0.1425   0.8626   0.0437
  -9.000  -0.2884   0.03656   0.02855  -0.1421   0.8555   0.0445
  -8.750  -0.2648   0.03494   0.02685  -0.1422   0.8508   0.0453
  -8.500  -0.2405   0.03355   0.02536  -0.1423   0.8464   0.0460
  -8.250  -0.2215   0.03254   0.02428  -0.1415   0.8390   0.0470
  -8.000  -0.1963   0.03141   0.02305  -0.1416   0.8341   0.0486
  -7.750  -0.1715   0.03041   0.02194  -0.1414   0.8291   0.0499
  -7.500  -0.1509   0.02967   0.02112  -0.1404   0.8219   0.0508
  -7.250  -0.1252   0.02886   0.02023  -0.1399   0.8170   0.0516
  -7.000  -0.1023   0.02815   0.01957  -0.1391   0.8113   0.0525
  -6.750  -0.0813   0.02755   0.01902  -0.1383   0.8038   0.0538
  -6.500  -0.0539   0.02680   0.01824  -0.1387   0.7987   0.0559
  -6.250  -0.0315   0.02625   0.01764  -0.1385   0.7906   0.0578
  -6.000  -0.0045   0.02555   0.01681  -0.1390   0.7839   0.0594
  -5.750   0.0240   0.02475   0.01590  -0.1401   0.7777   0.0611
  -5.500   0.0496   0.02403   0.01511  -0.1409   0.7692   0.0635
  -5.250   0.0815   0.02320   0.01414  -0.1424   0.7637   0.0670
  -5.000   0.1069   0.02263   0.01353  -0.1429   0.7542   0.0728
  -4.750   0.1385   0.02178   0.01263  -0.1444   0.7475   0.0880
  -4.500   0.1659   0.02087   0.01178  -0.1456   0.7379   0.1258
  -4.250   0.1971   0.01977   0.01154  -0.1477   0.7305   0.3215
  -4.000   0.2238   0.01992   0.01159  -0.1475   0.7203   0.3550
  -3.750   0.2546   0.01993   0.01139  -0.1478   0.7130   0.3747
  -3.500   0.2803   0.02017   0.01156  -0.1473   0.7024   0.3905
  -3.250   0.3094   0.02029   0.01156  -0.1472   0.6947   0.4031
  -3.000   0.3359   0.02043   0.01158  -0.1470   0.6843   0.4145
  -2.750   0.3638   0.02049   0.01153  -0.1468   0.6756   0.4224
  -2.500   0.3914   0.02059   0.01152  -0.1466   0.6664   0.4328
  -2.250   0.4186   0.02078   0.01160  -0.1464   0.6575   0.4452
  -2.000   0.4453   0.02094   0.01174  -0.1459   0.6497   0.4538
  -1.750   0.4734   0.02098   0.01164  -0.1461   0.6419   0.4615
  -1.500   0.5022   0.02089   0.01140  -0.1465   0.6348   0.4655
  -1.250   0.5304   0.02085   0.01127  -0.1466   0.6285   0.4684
  -1.000   0.5575   0.02088   0.01122  -0.1467   0.6212   0.4718
  -0.750   0.5872   0.02083   0.01102  -0.1471   0.6157   0.4761
  -0.500   0.6150   0.02088   0.01094  -0.1475   0.6090   0.4810
  -0.250   0.6426   0.02091   0.01091  -0.1476   0.6030   0.4843
   0.000   0.6718   0.02091   0.01081  -0.1479   0.5983   0.4876
   0.250   0.6978   0.02105   0.01093  -0.1478   0.5921   0.4917
   0.500   0.7260   0.02112   0.01090  -0.1481   0.5866   0.4966
   0.750   0.7550   0.02116   0.01081  -0.1485   0.5812   0.5010
   1.000   0.7796   0.02131   0.01099  -0.1481   0.5742   0.5046
   1.250   0.8073   0.02138   0.01097  -0.1482   0.5681   0.5088
   1.500   0.8341   0.02152   0.01104  -0.1483   0.5620   0.5139
   1.750   0.8600   0.02169   0.01119  -0.1482   0.5560   0.5186
   2.000   0.8876   0.02181   0.01128  -0.1483   0.5512   0.5231
   2.250   0.9145   0.02199   0.01144  -0.1483   0.5465   0.5284
   2.500   0.9396   0.02223   0.01166  -0.1482   0.5410   0.5339
   2.750   0.9658   0.02239   0.01184  -0.1481   0.5360   0.5383
   3.250   1.0177   0.02285   0.01231  -0.1480   0.5270   0.5506
   3.500   1.0421   0.02310   0.01263  -0.1477   0.5224   0.5561
   3.750   1.0686   0.02332   0.01286  -0.1476   0.5182   0.5626
   4.000   1.0969   0.02353   0.01300  -0.1479   0.5139   0.5700
   4.250   1.1166   0.02387   0.01350  -0.1469   0.5081   0.5757
   4.500   1.1401   0.02413   0.01378  -0.1464   0.5023   0.5837
   4.750   1.1677   0.02431   0.01392  -0.1465   0.4975   0.5918
   5.000   1.1867   0.02471   0.01447  -0.1454   0.4926   0.6004
   5.250   1.2076   0.02506   0.01492  -0.1446   0.4875   0.6092
   5.500   1.2314   0.02531   0.01519  -0.1442   0.4825   0.6193
   5.750   1.2524   0.02563   0.01559  -0.1433   0.4773   0.6292
   6.000   1.2683   0.02608   0.01618  -0.1418   0.4711   0.6408
   6.250   1.2884   0.02637   0.01654  -0.1408   0.4656   0.6532
   6.500   1.3074   0.02671   0.01696  -0.1396   0.4604   0.6666
   6.750   1.3182   0.02724   0.01769  -0.1373   0.4549   0.6805
   7.000   1.3342   0.02767   0.01823  -0.1358   0.4497   0.6966
   7.250   1.3548   0.02793   0.01857  -0.1349   0.4454   0.7159
   7.500   1.3623   0.02873   0.01962  -0.1324   0.4395   0.7378
   7.750   1.3735   0.02928   0.02041  -0.1304   0.4339   0.7701
   8.000   1.3818   0.02932   0.02071  -0.1273   0.4290   1.0000
   8.250   1.3860   0.03059   0.02212  -0.1250   0.4215   1.0000
   8.500   1.3973   0.03146   0.02302  -0.1234   0.4145   1.0000
   8.750   1.4022   0.03281   0.02448  -0.1214   0.4066   1.0000
   9.000   1.4099   0.03401   0.02575  -0.1197   0.3988   1.0000
   9.250   1.4129   0.03564   0.02750  -0.1178   0.3905   1.0000
   9.500   1.4192   0.03705   0.02895  -0.1161   0.3820   1.0000
   9.750   1.4184   0.03916   0.03118  -0.1142   0.3721   1.0000
  10.000   1.4212   0.04101   0.03308  -0.1126   0.3623   1.0000
  10.250   1.4231   0.04299   0.03511  -0.1111   0.3517   1.0000
  10.500   1.4212   0.04542   0.03760  -0.1095   0.3399   1.0000
  10.750   1.4209   0.04776   0.03997  -0.1080   0.3282   1.0000
  11.000   1.4212   0.05009   0.04231  -0.1067   0.3170   1.0000
  11.250   1.4219   0.05244   0.04462  -0.1055   0.3062   1.0000
  11.500   1.4203   0.05517   0.04736  -0.1043   0.2957   1.0000
  11.750   1.4195   0.05784   0.05004  -0.1033   0.2860   1.0000
  12.000   1.4192   0.06044   0.05257  -0.1023   0.2764   1.0000
  12.250   1.4161   0.06356   0.05570  -0.1014   0.2665   1.0000
  12.500   1.4148   0.06644   0.05853  -0.1006   0.2572   1.0000
  12.750   1.4131   0.06949   0.06160  -0.1000   0.2486   1.0000
  13.000   1.4136   0.07224   0.06432  -0.0994   0.2408   1.0000
  13.250   1.4130   0.07533   0.06749  -0.0990   0.2334   1.0000
  13.500   1.4155   0.07786   0.07001  -0.0985   0.2267   1.0000
  13.750   1.4160   0.08091   0.07316  -0.0983   0.2203   1.0000
  14.000   1.4152   0.08409   0.07640  -0.0981   0.2130   1.0000
  14.250   1.4151   0.08713   0.07946  -0.0979   0.2056   1.0000
  14.500   1.4125   0.09075   0.08322  -0.0980   0.1980   1.0000
  14.750   1.4123   0.09389   0.08638  -0.0980   0.1908   1.0000
  15.000   1.4102   0.09761   0.09031  -0.0984   0.1831   1.0000
  15.250   1.4079   0.10124   0.09406  -0.0987   0.1742   1.0000
  15.500   1.4045   0.10515   0.09811  -0.0992   0.1611   1.0000
  15.750   1.3983   0.10936   0.10229  -0.0999   0.1438   1.0000
  16.000   1.3889   0.11403   0.10682  -0.1007   0.1337   1.0000
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