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GOE 449 AIRFOIL (goe449-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: GOE 449 AIRFOIL (goe449-il)
Reynolds number: 200,000
Max Cl/Cd: 70.41 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe449-il-200000.txt
Download as CSV file: xf-goe449-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 449 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.0673   0.10024   0.09637  -0.1089   0.9472   0.0855
 -10.500  -0.0494   0.09710   0.09322  -0.1118   0.9444   0.0878
 -10.250  -0.0821   0.08745   0.08359  -0.1284   0.9403   0.0935
 -10.000  -0.0427   0.08523   0.08134  -0.1270   0.9398   0.0945
  -9.750  -0.0104   0.08240   0.07847  -0.1295   0.9389   0.0959
  -9.500  -0.2734   0.04652   0.04158  -0.1440   0.9068   0.0651
  -9.250  -0.2872   0.04470   0.03965  -0.1389   0.8958   0.0648
  -9.000  -0.2833   0.04062   0.03520  -0.1385   0.8911   0.0646
  -8.750  -0.2922   0.03830   0.03256  -0.1340   0.8828   0.0647
  -8.500  -0.2943   0.03602   0.02984  -0.1304   0.8761   0.0651
  -8.250  -0.2742   0.03345   0.02704  -0.1305   0.8735   0.0661
  -8.000  -0.2421   0.03200   0.02555  -0.1321   0.8717   0.0673
  -7.750  -0.2516   0.03172   0.02518  -0.1256   0.8617   0.0677
  -7.500  -0.2288   0.03018   0.02343  -0.1253   0.8583   0.0687
  -7.250  -0.2006   0.02853   0.02149  -0.1257   0.8559   0.0702
  -7.000  -0.1699   0.02699   0.01960  -0.1265   0.8540   0.0722
  -6.750  -0.1780   0.02700   0.01943  -0.1200   0.8440   0.0731
  -6.500  -0.1491   0.02569   0.01808  -0.1205   0.8409   0.0753
  -6.250  -0.1144   0.02478   0.01712  -0.1218   0.8387   0.0778
  -6.000  -0.0777   0.02374   0.01588  -0.1234   0.8368   0.0811
  -5.750  -0.0757   0.02375   0.01573  -0.1184   0.8281   0.0828
  -5.500  -0.0479   0.02279   0.01487  -0.1186   0.8242   0.0863
  -5.250  -0.0138   0.02216   0.01414  -0.1197   0.8216   0.0914
  -5.000   0.0231   0.02121   0.01317  -0.1213   0.8195   0.0971
  -4.750   0.0346   0.02112   0.01308  -0.1182   0.8124   0.1013
  -4.500   0.0582   0.02057   0.01248  -0.1173   0.8071   0.1075
  -4.250   0.0934   0.02001   0.01192  -0.1186   0.8040   0.1157
  -4.000   0.1303   0.01927   0.01119  -0.1202   0.8015   0.1244
  -3.750   0.1397   0.01934   0.01124  -0.1167   0.7936   0.1305
  -3.500   0.1664   0.01883   0.01079  -0.1164   0.7887   0.1391
  -3.250   0.2018   0.01830   0.01022  -0.1177   0.7855   0.1503
  -3.000   0.2405   0.01778   0.00968  -0.1196   0.7828   0.1636
  -2.750   0.2444   0.01774   0.00976  -0.1150   0.7730   0.1718
  -2.500   0.2764   0.01723   0.00930  -0.1156   0.7688   0.1884
  -2.250   0.3125   0.01668   0.00880  -0.1171   0.7657   0.2138
  -2.000   0.3204   0.01662   0.00889  -0.1132   0.7567   0.2375
  -1.750   0.3473   0.01603   0.00852  -0.1130   0.7516   0.2919
  -1.500   0.3769   0.01517   0.00813  -0.1134   0.7480   0.4094
  -1.250   0.3793   0.01489   0.00828  -0.1084   0.7384   0.5178
  -1.000   0.3986   0.01414   0.00826  -0.1059   0.7334   0.7181
  -0.750   0.4489   0.01394   0.00830  -0.1090   0.7301   0.8470
  -0.500   0.4742   0.01424   0.00865  -0.1079   0.7212   0.8947
  -0.250   0.5232   0.01431   0.00859  -0.1113   0.7160   0.9260
   0.000   0.5877   0.01443   0.00854  -0.1180   0.7115   0.9439
   0.250   0.6391   0.01467   0.00873  -0.1226   0.7033   0.9584
   0.500   0.7109   0.01468   0.00858  -0.1311   0.6978   0.9714
   0.750   0.7756   0.01474   0.00854  -0.1386   0.6912   0.9841
   1.000   0.8377   0.01466   0.00836  -0.1458   0.6838   0.9953
   1.250   0.8854   0.01448   0.00804  -0.1501   0.6783   1.0000
   1.500   0.8916   0.01462   0.00820  -0.1463   0.6699   1.0000
   1.750   0.9119   0.01459   0.00808  -0.1450   0.6635   1.0000
   2.000   0.9267   0.01468   0.00813  -0.1428   0.6569   1.0000
   2.250   0.9398   0.01477   0.00819  -0.1402   0.6498   1.0000
   2.500   0.9649   0.01475   0.00805  -0.1398   0.6444   1.0000
   2.750   0.9718   0.01495   0.00828  -0.1359   0.6371   1.0000
   3.000   0.9896   0.01500   0.00828  -0.1341   0.6307   1.0000
   3.250   1.0109   0.01507   0.00827  -0.1330   0.6249   1.0000
   3.500   1.0179   0.01525   0.00846  -0.1291   0.6174   1.0000
   3.750   1.0417   0.01526   0.00837  -0.1283   0.6111   1.0000
   4.000   1.0494   0.01546   0.00858  -0.1245   0.6039   1.0000
   4.250   1.0653   0.01557   0.00865  -0.1223   0.5973   1.0000
   4.500   1.0905   0.01569   0.00868  -0.1218   0.5918   1.0000
   4.750   1.0948   0.01593   0.00897  -0.1174   0.5850   1.0000
   5.000   1.1155   0.01607   0.00906  -0.1161   0.5792   1.0000
   5.250   1.1372   0.01628   0.00922  -0.1151   0.5737   1.0000
   5.500   1.1446   0.01653   0.00951  -0.1112   0.5672   1.0000
   5.750   1.1684   0.01669   0.00960  -0.1106   0.5613   1.0000
   6.000   1.1849   0.01695   0.00986  -0.1085   0.5553   1.0000
   6.250   1.1952   0.01720   0.01013  -0.1053   0.5488   1.0000
   6.500   1.2238   0.01738   0.01024  -0.1056   0.5429   1.0000
   6.750   1.2306   0.01770   0.01060  -0.1017   0.5362   1.0000
   7.000   1.2441   0.01791   0.01080  -0.0990   0.5289   1.0000
   7.250   1.2657   0.01813   0.01098  -0.0980   0.5218   1.0000
   7.500   1.2650   0.01841   0.01130  -0.0926   0.5145   1.0000
   7.750   1.2940   0.01859   0.01139  -0.0930   0.5073   1.0000
   8.000   1.2897   0.01894   0.01183  -0.0872   0.4999   1.0000
   8.250   1.3042   0.01916   0.01203  -0.0849   0.4922   1.0000
   8.500   1.3113   0.01950   0.01239  -0.0813   0.4841   1.0000
   8.750   1.3191   0.01981   0.01272  -0.0780   0.4760   1.0000
   9.000   1.3326   0.02014   0.01305  -0.0758   0.4685   1.0000
   9.250   1.3362   0.02060   0.01357  -0.0719   0.4603   1.0000
   9.500   1.3536   0.02090   0.01383  -0.0704   0.4529   1.0000
   9.750   1.3527   0.02152   0.01455  -0.0661   0.4441   1.0000
  10.000   1.3681   0.02187   0.01486  -0.0644   0.4361   1.0000
  10.250   1.3671   0.02262   0.01571  -0.0604   0.4266   1.0000
  10.500   1.3781   0.02314   0.01621  -0.0582   0.4178   1.0000
  10.750   1.3804   0.02392   0.01704  -0.0549   0.4077   1.0000
  11.000   1.3860   0.02472   0.01785  -0.0523   0.3978   1.0000
  11.250   1.3951   0.02540   0.01847  -0.0501   0.3879   1.0000
  11.500   1.3958   0.02650   0.01965  -0.0471   0.3770   1.0000
  11.750   1.4023   0.02743   0.02056  -0.0448   0.3667   1.0000
  12.000   1.4083   0.02843   0.02153  -0.0426   0.3563   1.0000
  12.250   1.4115   0.02965   0.02279  -0.0403   0.3458   1.0000
  12.500   1.4192   0.03069   0.02378  -0.0385   0.3361   1.0000
  12.750   1.4222   0.03202   0.02514  -0.0363   0.3258   1.0000
  13.000   1.4267   0.03335   0.02648  -0.0344   0.3160   1.0000
  13.250   1.4330   0.03458   0.02761  -0.0327   0.3060   1.0000
  13.500   1.4322   0.03635   0.02947  -0.0306   0.2958   1.0000
  13.750   1.4353   0.03789   0.03098  -0.0289   0.2859   1.0000
  14.000   1.4366   0.03963   0.03271  -0.0272   0.2761   1.0000
  14.250   1.4371   0.04152   0.03466  -0.0256   0.2665   1.0000
  14.500   1.4419   0.04307   0.03611  -0.0242   0.2575   1.0000
  14.750   1.4407   0.04526   0.03841  -0.0228   0.2487   1.0000
  15.000   1.4448   0.04695   0.04004  -0.0216   0.2403   1.0000
  15.250   1.4433   0.04927   0.04245  -0.0204   0.2318   1.0000
  15.500   1.4455   0.05125   0.04439  -0.0193   0.2236   1.0000
  15.750   1.4445   0.05364   0.04686  -0.0184   0.2158   1.0000
  16.000   1.4473   0.05564   0.04881  -0.0175   0.2086   1.0000
  16.250   1.4455   0.05825   0.05152  -0.0168   0.2014   1.0000
  16.500   1.4498   0.06013   0.05332  -0.0161   0.1949   1.0000
  16.750   1.4472   0.06297   0.05632  -0.0156   0.1887   1.0000
  17.000   1.4493   0.06521   0.05853  -0.0151   0.1828   1.0000
  17.250   1.4502   0.06768   0.06109  -0.0148   0.1774   1.0000
  17.500   1.4485   0.07052   0.06402  -0.0146   0.1718   1.0000
  17.750   1.4545   0.07232   0.06571  -0.0142   0.1667   1.0000
  18.000   1.4511   0.07551   0.06909  -0.0142   0.1620   1.0000
  18.250   1.4499   0.07839   0.07205  -0.0143   0.1571   1.0000
  18.500   1.4524   0.08070   0.07431  -0.0142   0.1521   1.0000
  18.750   1.4477   0.08417   0.07794  -0.0145   0.1474   1.0000
  19.000   1.4462   0.08715   0.08096  -0.0148   0.1428   1.0000
  19.250   1.4477   0.08966   0.08346  -0.0149   0.1383   1.0000
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