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GOE 229 (MVA H.39) AIRFOIL (goe229-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 229 (MVA H.39) AIRFOIL (goe229-il)
Reynolds number: 100,000
Max Cl/Cd: 38.52 at α=2.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe229-il-100000-n5.txt
Download as CSV file: xf-goe229-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 229 (MVA H.39) 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  -0.1942   0.09270   0.08794  -0.1018   0.9572   0.0342
 -11.750  -0.2268   0.08111   0.07623  -0.1102   0.9492   0.0336
 -11.500  -0.2549   0.07114   0.06605  -0.1195   0.9420   0.0332
 -11.250  -0.2765   0.06431   0.05901  -0.1255   0.9306   0.0331
 -11.000  -0.2904   0.05848   0.05291  -0.1315   0.9209   0.0332
 -10.750  -0.3021   0.05406   0.04824  -0.1354   0.9088   0.0335
 -10.500  -0.3140   0.05072   0.04466  -0.1375   0.8960   0.0340
 -10.250  -0.3172   0.04734   0.04092  -0.1414   0.8863   0.0347
 -10.000  -0.3162   0.04480   0.03798  -0.1433   0.8760   0.0354
  -9.750  -0.3062   0.04222   0.03506  -0.1447   0.8687   0.0363
  -9.500  -0.2920   0.03999   0.03276  -0.1445   0.8609   0.0372
  -9.250  -0.2702   0.03795   0.03057  -0.1454   0.8559   0.0382
  -9.000  -0.2553   0.03656   0.02906  -0.1449   0.8475   0.0395
  -8.750  -0.2334   0.03510   0.02744  -0.1453   0.8414   0.0415
  -8.500  -0.2102   0.03372   0.02585  -0.1457   0.8358   0.0434
  -8.250  -0.1911   0.03265   0.02462  -0.1449   0.8279   0.0447
  -8.000  -0.1651   0.03145   0.02326  -0.1450   0.8228   0.0459
  -7.750  -0.1469   0.03033   0.02224  -0.1434   0.8157   0.0482
  -7.500  -0.1253   0.02948   0.02141  -0.1427   0.8089   0.0504
  -7.250  -0.0986   0.02862   0.02051  -0.1427   0.8042   0.0525
  -7.000  -0.0808   0.02812   0.01998  -0.1414   0.7955   0.0540
  -6.750  -0.0549   0.02743   0.01917  -0.1416   0.7898   0.0566
  -6.500  -0.0315   0.02661   0.01832  -0.1419   0.7832   0.0593
  -6.250  -0.0073   0.02574   0.01738  -0.1427   0.7757   0.0619
  -6.000   0.0239   0.02476   0.01622  -0.1445   0.7705   0.0650
  -5.750   0.0480   0.02410   0.01545  -0.1451   0.7620   0.0688
  -5.500   0.0784   0.02313   0.01446  -0.1469   0.7558   0.0774
  -5.250   0.1080   0.02226   0.01357  -0.1484   0.7494   0.0978
  -5.000   0.1366   0.02043   0.01246  -0.1515   0.7420   0.2379
  -4.750   0.1680   0.02034   0.01257  -0.1522   0.7367   0.3253
  -4.500   0.1944   0.02056   0.01271  -0.1519   0.7288   0.3556
  -4.250   0.2244   0.02069   0.01264  -0.1523   0.7221   0.3787
  -4.000   0.2540   0.02091   0.01271  -0.1525   0.7158   0.3959
  -3.750   0.2792   0.02117   0.01294  -0.1518   0.7079   0.4039
  -3.500   0.3101   0.02123   0.01282  -0.1522   0.7024   0.4159
  -3.250   0.3356   0.02161   0.01314  -0.1517   0.6951   0.4298
  -3.000   0.3613   0.02205   0.01362  -0.1508   0.6886   0.4413
  -2.750   0.3923   0.02211   0.01352  -0.1512   0.6838   0.4519
  -2.500   0.4155   0.02223   0.01363  -0.1505   0.6753   0.4562
  -2.250   0.4456   0.02204   0.01328  -0.1511   0.6685   0.4608
  -2.000   0.4728   0.02192   0.01297  -0.1514   0.6600   0.4663
  -1.750   0.5005   0.02180   0.01278  -0.1513   0.6519   0.4695
  -1.500   0.5254   0.02177   0.01270  -0.1509   0.6424   0.4728
  -1.250   0.5539   0.02161   0.01239  -0.1510   0.6334   0.4769
  -1.000   0.5784   0.02156   0.01224  -0.1507   0.6220   0.4818
  -0.750   0.6040   0.02143   0.01196  -0.1504   0.6095   0.4858
  -0.500   0.6280   0.02134   0.01176  -0.1496   0.5950   0.4887
  -0.250   0.6517   0.02129   0.01158  -0.1489   0.5802   0.4924
   0.000   0.6753   0.02131   0.01149  -0.1483   0.5669   0.4968
   0.250   0.6996   0.02135   0.01140  -0.1480   0.5550   0.5016
   0.500   0.7228   0.02141   0.01138  -0.1473   0.5428   0.5046
   0.750   0.7448   0.02151   0.01137  -0.1464   0.5289   0.5078
   1.000   0.7661   0.02166   0.01145  -0.1454   0.5152   0.5119
   1.250   0.7881   0.02182   0.01154  -0.1447   0.5034   0.5166
   1.500   0.8108   0.02198   0.01161  -0.1441   0.4931   0.5210
   1.750   0.8313   0.02218   0.01181  -0.1431   0.4814   0.5242
   2.000   0.8511   0.02241   0.01202  -0.1420   0.4683   0.5279
   2.250   0.8697   0.02268   0.01223  -0.1408   0.4529   0.5322
   2.500   0.8860   0.02300   0.01245  -0.1392   0.4337   0.5372
   2.750   0.8999   0.02340   0.01278  -0.1372   0.4101   0.5409
   3.000   0.9133   0.02392   0.01318  -0.1352   0.3803   0.5450
   3.250   0.9107   0.02539   0.01414  -0.1313   0.3101   0.5488
   3.500   0.9034   0.02750   0.01575  -0.1274   0.2454   0.5526
   3.750   0.9123   0.02871   0.01681  -0.1256   0.2235   0.5569
   4.000   0.9231   0.02979   0.01783  -0.1240   0.2087   0.5606
   4.250   0.9344   0.03087   0.01887  -0.1225   0.1950   0.5654
   4.500   0.9437   0.03216   0.02008  -0.1210   0.1663   0.5708
   4.750   0.9431   0.03421   0.02189  -0.1187   0.1244   0.5755
   5.000   0.9501   0.03572   0.02336  -0.1172   0.1158   0.5801
   5.250   0.9611   0.03698   0.02465  -0.1161   0.1129   0.5859
   5.500   0.9725   0.03828   0.02597  -0.1151   0.1105   0.5924
   5.750   0.9833   0.03959   0.02735  -0.1141   0.1086   0.5975
   6.000   0.9945   0.04092   0.02874  -0.1132   0.1072   0.6040
   6.250   1.0060   0.04229   0.03016  -0.1124   0.1062   0.6114
   6.500   1.0162   0.04373   0.03170  -0.1115   0.1049   0.6183
   6.750   1.0263   0.04526   0.03330  -0.1106   0.1037   0.6269
   7.000   1.0363   0.04679   0.03491  -0.1098   0.1028   0.6348
   7.250   1.0466   0.04835   0.03655  -0.1091   0.1021   0.6445
   7.500   1.0568   0.04992   0.03820  -0.1084   0.1016   0.6537
   7.750   1.0676   0.05147   0.03987  -0.1079   0.1012   0.6645
   8.000   1.0780   0.05307   0.04158  -0.1073   0.1009   0.6763
   8.250   1.0883   0.05469   0.04332  -0.1067   0.1006   0.6894
   8.500   1.0984   0.05635   0.04512  -0.1062   0.1003   0.7047
   8.750   1.1082   0.05803   0.04695  -0.1057   0.1001   0.7233
   9.000   1.1175   0.05968   0.04882  -0.1051   0.0999   0.7490
   9.250   1.1216   0.06106   0.05055  -0.1034   0.0998   0.8605
   9.500   1.1267   0.06289   0.05247  -0.1026   0.0997   1.0000
   9.750   1.1363   0.06489   0.05451  -0.1025   0.0996   1.0000
  10.000   1.1457   0.06691   0.05659  -0.1023   0.0996   1.0000
  10.250   1.1547   0.06897   0.05871  -0.1021   0.0995   1.0000
  10.500   1.1635   0.07107   0.06090  -0.1019   0.0995   1.0000
  10.750   1.1720   0.07320   0.06311  -0.1018   0.0995   1.0000
  11.000   1.1802   0.07538   0.06537  -0.1016   0.0995   1.0000
  11.250   1.1883   0.07759   0.06767  -0.1015   0.0993   1.0000
  11.500   1.1961   0.07985   0.07002  -0.1014   0.0980   1.0000
  11.750   1.2030   0.08221   0.07246  -0.1013   0.0957   1.0000
  12.000   1.2083   0.08478   0.07512  -0.1012   0.0927   1.0000
  12.250   1.2140   0.08732   0.07773  -0.1012   0.0898   1.0000
  12.500   1.2257   0.08912   0.07969  -0.1012   0.0852   1.0000
  12.750   1.2196   0.09322   0.08373  -0.1013   0.0642   1.0000
  13.000   1.2158   0.09713   0.08766  -0.1015   0.0625   1.0000
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