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GOE 223 (MVA H.34) AIRFOIL (goe223-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 223 (MVA H.34) AIRFOIL (goe223-il)
Reynolds number: 200,000
Max Cl/Cd: 67 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe223-il-200000-n5.txt
Download as CSV file: xf-goe223-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.000  -0.3155   0.07893   0.07492  -0.1038   0.9314   0.0256
 -12.750  -0.3511   0.06955   0.06532  -0.1107   0.9221   0.0255
 -12.500  -0.3780   0.06255   0.05809  -0.1160   0.9128   0.0255
 -12.250  -0.3998   0.05670   0.05200  -0.1207   0.9020   0.0256
 -12.000  -0.4179   0.05165   0.04667  -0.1249   0.8922   0.0258
 -11.750  -0.4327   0.04723   0.04193  -0.1289   0.8824   0.0261
 -11.250  -0.4369   0.04123   0.03550  -0.1338   0.8662   0.0267
 -11.000  -0.4253   0.03913   0.03329  -0.1357   0.8594   0.0271
 -10.750  -0.4110   0.03727   0.03131  -0.1373   0.8527   0.0275
 -10.500  -0.3954   0.03553   0.02939  -0.1385   0.8475   0.0280
 -10.250  -0.3786   0.03395   0.02765  -0.1396   0.8405   0.0287
 -10.000  -0.3606   0.03239   0.02585  -0.1406   0.8343   0.0296
  -9.750  -0.3411   0.03091   0.02408  -0.1415   0.8284   0.0304
  -9.500  -0.3201   0.02963   0.02251  -0.1423   0.8220   0.0311
  -9.250  -0.2977   0.02829   0.02099  -0.1426   0.8172   0.0316
  -9.000  -0.2747   0.02706   0.01974  -0.1425   0.8130   0.0323
  -8.750  -0.2514   0.02611   0.01878  -0.1427   0.8074   0.0331
  -8.500  -0.2272   0.02524   0.01784  -0.1428   0.8021   0.0340
  -8.250  -0.2023   0.02439   0.01688  -0.1429   0.7976   0.0349
  -8.000  -0.1779   0.02362   0.01604  -0.1430   0.7915   0.0355
  -7.750  -0.1529   0.02288   0.01522  -0.1430   0.7857   0.0361
  -7.500  -0.1268   0.02222   0.01443  -0.1432   0.7809   0.0368
  -7.250  -0.1019   0.02151   0.01370  -0.1433   0.7749   0.0376
  -7.000  -0.0773   0.02070   0.01293  -0.1435   0.7689   0.0385
  -6.750  -0.0508   0.02002   0.01220  -0.1439   0.7637   0.0393
  -6.500  -0.0245   0.01941   0.01157  -0.1444   0.7569   0.0400
  -6.250   0.0028   0.01881   0.01091  -0.1450   0.7501   0.0407
  -6.000   0.0307   0.01824   0.01027  -0.1457   0.7434   0.0415
  -5.750   0.0586   0.01774   0.00969  -0.1464   0.7352   0.0427
  -5.500   0.0873   0.01729   0.00912  -0.1471   0.7280   0.0438
  -5.250   0.1156   0.01677   0.00854  -0.1478   0.7192   0.0450
  -5.000   0.1446   0.01633   0.00798  -0.1485   0.7113   0.0462
  -4.750   0.1731   0.01598   0.00755  -0.1491   0.7015   0.0477
  -4.500   0.2019   0.01568   0.00714  -0.1495   0.6920   0.0495
  -4.250   0.2305   0.01543   0.00677  -0.1499   0.6812   0.0519
  -4.000   0.2591   0.01512   0.00644  -0.1504   0.6692   0.0585
  -3.750   0.2879   0.01458   0.00601  -0.1512   0.6569   0.1130
  -3.500   0.3169   0.01350   0.00555  -0.1528   0.6444   0.2953
  -3.250   0.3449   0.01352   0.00555  -0.1529   0.6318   0.3317
  -3.000   0.3728   0.01359   0.00552  -0.1529   0.6192   0.3490
  -2.750   0.4004   0.01369   0.00549  -0.1529   0.6071   0.3623
  -2.500   0.4279   0.01382   0.00548  -0.1529   0.5961   0.3745
  -2.250   0.4552   0.01396   0.00552  -0.1528   0.5855   0.3835
  -2.000   0.4827   0.01412   0.00551  -0.1528   0.5758   0.3938
  -1.750   0.5094   0.01430   0.00562  -0.1526   0.5667   0.4024
  -1.500   0.5369   0.01445   0.00564  -0.1526   0.5584   0.4102
  -1.250   0.5637   0.01463   0.00576  -0.1525   0.5510   0.4180
  -1.000   0.5911   0.01483   0.00586  -0.1525   0.5442   0.4283
  -0.750   0.6179   0.01498   0.00598  -0.1523   0.5374   0.4345
  -0.500   0.6449   0.01514   0.00604  -0.1523   0.5316   0.4387
  -0.250   0.6726   0.01522   0.00608  -0.1524   0.5264   0.4425
   0.000   0.7002   0.01533   0.00610  -0.1525   0.5216   0.4462
   0.250   0.7273   0.01544   0.00617  -0.1526   0.5171   0.4489
   0.500   0.7546   0.01556   0.00626  -0.1526   0.5131   0.4518
   0.750   0.7819   0.01566   0.00636  -0.1527   0.5087   0.4552
   1.000   0.8091   0.01578   0.00646  -0.1527   0.5045   0.4592
   1.250   0.8362   0.01593   0.00654  -0.1527   0.5006   0.4633
   1.500   0.8630   0.01609   0.00666  -0.1527   0.4967   0.4665
   1.750   0.8895   0.01617   0.00680  -0.1527   0.4921   0.4698
   2.000   0.9156   0.01631   0.00694  -0.1525   0.4868   0.4735
   2.250   0.9414   0.01648   0.00707  -0.1524   0.4819   0.4779
   2.500   0.9674   0.01663   0.00721  -0.1522   0.4772   0.4824
   2.750   0.9930   0.01674   0.00740  -0.1520   0.4725   0.4863
   3.000   1.0187   0.01689   0.00758  -0.1518   0.4685   0.4906
   3.250   1.0443   0.01707   0.00775  -0.1517   0.4650   0.4953
   3.500   1.0697   0.01725   0.00793  -0.1515   0.4614   0.5000
   3.750   1.0947   0.01738   0.00816  -0.1512   0.4568   0.5045
   4.000   1.1190   0.01754   0.00838  -0.1508   0.4520   0.5101
   4.250   1.1430   0.01775   0.00859  -0.1503   0.4478   0.5163
   4.500   1.1666   0.01793   0.00884  -0.1498   0.4436   0.5216
   4.750   1.1902   0.01811   0.00911  -0.1493   0.4387   0.5278
   5.250   1.2341   0.01856   0.00965  -0.1478   0.4284   0.5406
   5.500   1.2553   0.01877   0.00996  -0.1469   0.4225   0.5482
   5.750   1.2744   0.01902   0.01029  -0.1456   0.4163   0.5561
   6.000   1.2934   0.01932   0.01065  -0.1444   0.4096   0.5652
   6.250   1.3125   0.01965   0.01106  -0.1433   0.4009   0.5746
   6.500   1.3309   0.02003   0.01151  -0.1421   0.3922   0.5851
   6.750   1.3481   0.02047   0.01201  -0.1408   0.3824   0.5956
   7.000   1.3641   0.02098   0.01256  -0.1394   0.3698   0.6074
   7.250   1.3764   0.02167   0.01325  -0.1375   0.3529   0.6198
   7.500   1.3864   0.02252   0.01408  -0.1354   0.3335   0.6329
   7.750   1.3929   0.02362   0.01512  -0.1330   0.3108   0.6465
   8.000   1.3962   0.02500   0.01642  -0.1304   0.2884   0.6608
   8.250   1.4003   0.02643   0.01781  -0.1280   0.2719   0.6759
   8.750   1.4144   0.02909   0.02056  -0.1243   0.2520   0.7111
   9.000   1.4201   0.03056   0.02209  -0.1224   0.2441   0.7338
   9.250   1.4269   0.03190   0.02357  -0.1207   0.2369   0.7746
   9.500   1.4257   0.03318   0.02505  -0.1176   0.2303   1.0000
   9.750   1.4299   0.03501   0.02688  -0.1161   0.2236   1.0000
  10.000   1.4369   0.03666   0.02857  -0.1148   0.2171   1.0000
  10.250   1.4402   0.03865   0.03057  -0.1133   0.2107   1.0000
  10.500   1.4456   0.04054   0.03249  -0.1121   0.2052   1.0000
  10.750   1.4526   0.04234   0.03434  -0.1111   0.1988   1.0000
  11.000   1.4547   0.04464   0.03665  -0.1099   0.1922   1.0000
  11.250   1.4624   0.04646   0.03854  -0.1090   0.1854   1.0000
  11.500   1.4658   0.04874   0.04086  -0.1081   0.1747   1.0000
  11.750   1.4652   0.05151   0.04360  -0.1071   0.1486   1.0000
  12.000   1.4502   0.05590   0.04781  -0.1058   0.1297   1.0000
  12.250   1.4459   0.05921   0.05110  -0.1049   0.1241   1.0000
  12.500   1.4423   0.06254   0.05444  -0.1042   0.1194   1.0000
  12.750   1.4404   0.06574   0.05768  -0.1036   0.1155   1.0000
  13.000   1.4401   0.06880   0.06080  -0.1031   0.1122   1.0000
  13.250   1.4395   0.07192   0.06399  -0.1027   0.1096   1.0000
  13.500   1.4374   0.07527   0.06740  -0.1024   0.1070   1.0000
  13.750   1.4359   0.07859   0.07079  -0.1021   0.1044   1.0000
  14.000   1.4404   0.08116   0.07348  -0.1020   0.1015   1.0000
  14.250   1.4408   0.08428   0.07667  -0.1018   0.0978   1.0000
  14.500   1.4356   0.08812   0.08057  -0.1018   0.0940   1.0000
  14.750   1.4427   0.09041   0.08296  -0.1017   0.0894   1.0000
  15.000   1.4472   0.09305   0.08569  -0.1017   0.0819   1.0000
  15.250   1.4310   0.09846   0.09085  -0.1021   0.0406   1.0000
  15.500   1.4100   0.10462   0.09695  -0.1026   0.0249   1.0000
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