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GOE 675 AIRFOIL (goe675-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 675 AIRFOIL (goe675-il)
Reynolds number: 100,000
Max Cl/Cd: 52.23 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe675-il-100000-n5.txt
Download as CSV file: xf-goe675-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 675 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
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.1023   0.09837   0.09261  -0.0945   0.9437   0.0594
  -9.500  -0.0931   0.09427   0.08850  -0.0982   0.9406   0.0597
  -9.250  -0.0921   0.09091   0.08514  -0.0997   0.9339   0.0596
  -9.000  -0.0889   0.08706   0.08129  -0.1022   0.9283   0.0594
  -8.750  -0.0836   0.08269   0.07690  -0.1059   0.9241   0.0594
  -8.500  -0.0892   0.07921   0.07345  -0.1070   0.9160   0.0595
  -8.250  -0.0942   0.07504   0.06928  -0.1094   0.9088   0.0597
  -7.750  -0.1659   0.05003   0.04379  -0.1305   0.8869   0.0622
  -7.500  -0.1616   0.04902   0.04275  -0.1287   0.8788   0.0629
  -7.250  -0.1513   0.04593   0.03946  -0.1299   0.8731   0.0640
  -7.000  -0.1408   0.03968   0.03256  -0.1336   0.8690   0.0665
  -6.750  -0.1356   0.03571   0.02793  -0.1332   0.8620   0.0693
  -6.500  -0.1160   0.03541   0.02763  -0.1322   0.8565   0.0709
  -6.250  -0.0912   0.03370   0.02557  -0.1329   0.8530   0.0746
  -6.000  -0.0621   0.03225   0.02385  -0.1340   0.8505   0.0780
  -5.750  -0.0304   0.03130   0.02273  -0.1351   0.8485   0.0815
  -5.500  -0.0237   0.03045   0.02150  -0.1321   0.8393   0.0853
  -5.250   0.0036   0.03020   0.02133  -0.1322   0.8355   0.0881
  -5.000   0.0348   0.02938   0.02025  -0.1330   0.8328   0.0933
  -4.750   0.0687   0.02869   0.01948  -0.1342   0.8305   0.0976
  -4.500   0.0813   0.02869   0.01945  -0.1317   0.8211   0.1009
  -4.250   0.1122   0.02795   0.01844  -0.1321   0.8165   0.1067
  -4.000   0.1479   0.02739   0.01793  -0.1333   0.8131   0.1116
  -3.750   0.1677   0.02706   0.01742  -0.1318   0.8044   0.1162
  -3.500   0.1972   0.02634   0.01661  -0.1319   0.7987   0.1199
  -3.250   0.2321   0.02559   0.01581  -0.1329   0.7952   0.1234
  -3.000   0.2540   0.02528   0.01543  -0.1318   0.7881   0.1265
  -2.750   0.2794   0.02490   0.01492  -0.1312   0.7821   0.1298
  -2.500   0.3120   0.02424   0.01418  -0.1317   0.7784   0.1327
  -2.250   0.3468   0.02354   0.01349  -0.1327   0.7756   0.1358
  -2.000   0.3611   0.02361   0.01359  -0.1304   0.7657   0.1386
  -1.750   0.3927   0.02311   0.01303  -0.1307   0.7612   0.1430
  -1.500   0.4278   0.02250   0.01234  -0.1316   0.7580   0.1472
  -1.250   0.4434   0.02250   0.01243  -0.1295   0.7480   0.1503
  -1.000   0.4747   0.02202   0.01197  -0.1298   0.7431   0.1557
  -0.750   0.5030   0.02171   0.01162  -0.1296   0.7370   0.1626
  -0.500   0.5253   0.02152   0.01153  -0.1285   0.7284   0.1697
  -0.250   0.5592   0.02101   0.01101  -0.1291   0.7235   0.1810
   0.000   0.5786   0.02098   0.01109  -0.1276   0.7136   0.1923
   0.250   0.6098   0.02055   0.01073  -0.1279   0.7071   0.2142
   0.500   0.6325   0.02043   0.01075  -0.1268   0.6975   0.2455
   0.750   0.6629   0.02004   0.01049  -0.1270   0.6896   0.2983
   1.000   0.6867   0.01986   0.01051  -0.1262   0.6794   0.3608
   1.250   0.7164   0.01920   0.01030  -0.1263   0.6710   0.5013
   1.750   0.7711   0.01816   0.01007  -0.1247   0.6497   1.0000
   2.000   0.7950   0.01827   0.01005  -0.1238   0.6371   1.0000
   2.250   0.8194   0.01838   0.01004  -0.1230   0.6244   1.0000
   2.500   0.8469   0.01841   0.00992  -0.1227   0.6123   1.0000
   2.750   0.8730   0.01850   0.00986  -0.1221   0.5991   1.0000
   3.000   0.8958   0.01870   0.00996  -0.1211   0.5849   1.0000
   3.250   0.9200   0.01889   0.01004  -0.1203   0.5714   1.0000
   3.500   0.9452   0.01908   0.01008  -0.1197   0.5586   1.0000
   3.750   0.9695   0.01931   0.01019  -0.1190   0.5457   1.0000
   4.000   0.9917   0.01962   0.01041  -0.1180   0.5330   1.0000
   4.250   1.0157   0.01991   0.01059  -0.1173   0.5220   1.0000
   4.500   1.0394   0.02023   0.01079  -0.1165   0.5114   1.0000
   4.750   1.0618   0.02060   0.01109  -0.1156   0.5014   1.0000
   5.000   1.0861   0.02094   0.01131  -0.1150   0.4925   1.0000
   5.250   1.1075   0.02135   0.01169  -0.1140   0.4837   1.0000
   5.500   1.1313   0.02173   0.01198  -0.1134   0.4759   1.0000
   5.750   1.1535   0.02216   0.01237  -0.1125   0.4684   1.0000
   6.000   1.1750   0.02260   0.01278  -0.1116   0.4610   1.0000
   6.250   1.2014   0.02300   0.01306  -0.1114   0.4547   1.0000
   6.500   1.2200   0.02351   0.01364  -0.1101   0.4477   1.0000
   6.750   1.2424   0.02398   0.01407  -0.1093   0.4412   1.0000
   7.000   1.2676   0.02444   0.01446  -0.1090   0.4353   1.0000
   7.250   1.2852   0.02501   0.01510  -0.1076   0.4288   1.0000
   7.500   1.3066   0.02552   0.01560  -0.1067   0.4226   1.0000
   7.750   1.3314   0.02601   0.01603  -0.1064   0.4169   1.0000
   8.000   1.3463   0.02665   0.01678  -0.1046   0.4105   1.0000
   8.250   1.3658   0.02722   0.01737  -0.1035   0.4044   1.0000
   8.500   1.3912   0.02770   0.01779  -0.1033   0.3991   1.0000
   8.750   1.4027   0.02846   0.01869  -0.1012   0.3930   1.0000
   9.000   1.4194   0.02911   0.01940  -0.0997   0.3871   1.0000
   9.250   1.4426   0.02960   0.01984  -0.0992   0.3814   1.0000
   9.500   1.4503   0.03049   0.02089  -0.0967   0.3749   1.0000
   9.750   1.4625   0.03124   0.02171  -0.0947   0.3682   1.0000
  10.000   1.4806   0.03182   0.02226  -0.0936   0.3620   1.0000
  10.250   1.4845   0.03291   0.02353  -0.0908   0.3549   1.0000
  10.500   1.4954   0.03372   0.02438  -0.0889   0.3481   1.0000
  10.750   1.5052   0.03465   0.02538  -0.0869   0.3415   1.0000
  11.000   1.5106   0.03582   0.02669  -0.0846   0.3344   1.0000
  11.250   1.5228   0.03663   0.02750  -0.0830   0.3283   1.0000
  11.500   1.5260   0.03805   0.02909  -0.0807   0.3214   1.0000
  11.750   1.5318   0.03930   0.03043  -0.0787   0.3146   1.0000
  12.000   1.5377   0.04058   0.03178  -0.0768   0.3077   1.0000
  12.250   1.5381   0.04229   0.03363  -0.0746   0.2996   1.0000
  12.500   1.5420   0.04375   0.03512  -0.0727   0.2921   1.0000
  12.750   1.5407   0.04578   0.03730  -0.0708   0.2837   1.0000
  13.000   1.5425   0.04754   0.03910  -0.0690   0.2761   1.0000
  13.250   1.5397   0.04989   0.04160  -0.0674   0.2676   1.0000
  13.500   1.5399   0.05203   0.04380  -0.0659   0.2599   1.0000
  13.750   1.5365   0.05469   0.04658  -0.0645   0.2516   1.0000
  14.000   1.5342   0.05730   0.04926  -0.0633   0.2439   1.0000
  14.250   1.5291   0.06037   0.05245  -0.0623   0.2355   1.0000
  14.500   1.5232   0.06366   0.05582  -0.0615   0.2271   1.0000
  14.750   1.5159   0.06718   0.05940  -0.0608   0.2184   1.0000
  15.000   1.5060   0.07125   0.06361  -0.0604   0.2096   1.0000
  15.250   1.4970   0.07527   0.06766  -0.0602   0.2012   1.0000
  15.500   1.4849   0.07994   0.07246  -0.0603   0.1930   1.0000
  15.750   1.4738   0.08450   0.07710  -0.0605   0.1853   1.0000
  16.000   1.4604   0.08958   0.08227  -0.0610   0.1772   1.0000
  16.250   1.4472   0.09475   0.08752  -0.0618   0.1693   1.0000
  16.500   1.4344   0.09991   0.09272  -0.0627   0.1608   1.0000
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