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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 500,000
Max Cl/Cd: 92.87 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe198-il-500000-n5.txt
Download as CSV file: xf-goe198-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 198 (L.F.G. 5294) AIRFOIL                   
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2017   0.09874   0.09598  -0.0489   0.8779   0.0197
  -8.500  -0.1944   0.09573   0.09297  -0.0512   0.8737   0.0198
  -8.250  -0.1886   0.09272   0.08994  -0.0541   0.8693   0.0199
  -8.000  -0.1784   0.08971   0.08691  -0.0542   0.8662   0.0200
  -7.750  -0.1680   0.08717   0.08438  -0.0550   0.8619   0.0201
  -7.500  -0.1583   0.08483   0.08204  -0.0561   0.8575   0.0204
  -7.250  -0.1453   0.08230   0.07949  -0.0583   0.8538   0.0207
  -7.000  -0.1309   0.07967   0.07684  -0.0609   0.8502   0.0211
  -6.750  -0.1147   0.07686   0.07402  -0.0642   0.8458   0.0217
  -6.500  -0.0951   0.07367   0.07081  -0.0690   0.8411   0.0230
  -6.250  -0.0681   0.06974   0.06680  -0.0775   0.8365   0.0234
  -6.000  -0.0420   0.06598   0.06300  -0.0840   0.8314   0.0235
  -5.750  -0.0151   0.06230   0.05926  -0.0897   0.8259   0.0235
  -5.500   0.0122   0.05874   0.05562  -0.0946   0.8211   0.0236
  -5.250   0.0320   0.05564   0.05251  -0.0966   0.8161   0.0237
  -5.000   0.0526   0.05336   0.05020  -0.0979   0.8103   0.0240
  -4.750   0.0767   0.05111   0.04791  -0.1002   0.8052   0.0243
  -4.500   0.1034   0.04890   0.04566  -0.1030   0.8002   0.0250
  -4.250   0.1336   0.04639   0.04308  -0.1067   0.7944   0.0261
  -4.000   0.1823   0.04227   0.03875  -0.1151   0.7889   0.0278
  -3.750   0.2182   0.03905   0.03539  -0.1194   0.7821   0.0279
  -3.500   0.2517   0.03619   0.03239  -0.1226   0.7744   0.0279
  -3.250   0.2849   0.03349   0.02955  -0.1255   0.7675   0.0280
  -3.000   0.3145   0.03074   0.02669  -0.1280   0.7601   0.0284
  -2.750   0.3418   0.02946   0.02535  -0.1292   0.7524   0.0289
  -2.500   0.3774   0.02682   0.02252  -0.1317   0.7437   0.0273
  -2.250   0.4097   0.02475   0.02027  -0.1336   0.7330   0.0264
  -2.000   0.4450   0.02220   0.01745  -0.1357   0.7196   0.0259
  -1.750   0.4799   0.01977   0.01470  -0.1374   0.7043   0.0259
  -1.500   0.5143   0.01744   0.01200  -0.1389   0.6883   0.0259
  -1.250   0.5479   0.01523   0.00936  -0.1400   0.6711   0.0266
  -1.000   0.5803   0.01322   0.00686  -0.1410   0.6517   0.0266
  -0.750   0.6097   0.01239   0.00568  -0.1413   0.6285   0.0268
  -0.500   0.6381   0.01196   0.00497  -0.1413   0.6022   0.0272
  -0.250   0.6658   0.01177   0.00451  -0.1413   0.5752   0.0275
   0.000   0.6934   0.01167   0.00421  -0.1413   0.5524   0.0278
   0.250   0.7214   0.01149   0.00391  -0.1414   0.5369   0.0282
   0.500   0.7496   0.01129   0.00362  -0.1415   0.5254   0.0287
   0.750   0.7776   0.01121   0.00350  -0.1416   0.5135   0.0293
   1.000   0.8056   0.01119   0.00344  -0.1416   0.5005   0.0303
   1.250   0.8334   0.01118   0.00338  -0.1417   0.4866   0.0312
   1.500   0.8611   0.01120   0.00333  -0.1417   0.4686   0.0318
   1.750   0.8886   0.01127   0.00331  -0.1417   0.4477   0.0325
   2.000   0.9156   0.01141   0.00333  -0.1416   0.4189   0.0332
   2.250   0.9411   0.01171   0.00341  -0.1413   0.3751   0.0344
   2.500   0.9669   0.01200   0.00355  -0.1411   0.3473   0.0361
   2.750   0.9932   0.01223   0.00370  -0.1409   0.3308   0.0385
   3.250   1.0463   0.01263   0.00408  -0.1406   0.3068   0.0704
   3.500   1.0726   0.01284   0.00426  -0.1404   0.2960   0.0800
   3.750   1.0987   0.01307   0.00445  -0.1402   0.2841   0.0877
   4.000   1.1250   0.01325   0.00462  -0.1401   0.2723   0.0998
   4.250   1.1507   0.01239   0.00509  -0.1404   0.2579   0.8391
   4.750   1.1890   0.01352   0.00576  -0.1374   0.1619   1.0000
   5.000   1.2040   0.01495   0.00669  -0.1355   0.0708   1.0000
   5.250   1.2275   0.01540   0.00707  -0.1349   0.0622   1.0000
   5.500   1.2518   0.01575   0.00739  -0.1344   0.0599   1.0000
   5.750   1.2758   0.01610   0.00774  -0.1338   0.0582   1.0000
   6.000   1.2995   0.01647   0.00811  -0.1332   0.0568   1.0000
   6.250   1.3230   0.01684   0.00849  -0.1325   0.0557   1.0000
   6.500   1.3459   0.01723   0.00890  -0.1318   0.0548   1.0000
   6.750   1.3685   0.01764   0.00933  -0.1310   0.0541   1.0000
   7.000   1.3908   0.01803   0.00976  -0.1302   0.0538   1.0000
   7.250   1.4127   0.01844   0.01019  -0.1293   0.0532   1.0000
   7.500   1.4340   0.01886   0.01065  -0.1284   0.0522   1.0000
   7.750   1.4543   0.01931   0.01114  -0.1272   0.0511   1.0000
   8.000   1.4738   0.01980   0.01167  -0.1260   0.0502   1.0000
   8.250   1.4922   0.02033   0.01223  -0.1246   0.0493   1.0000
   8.500   1.5094   0.02090   0.01284  -0.1230   0.0484   1.0000
   8.750   1.5236   0.02154   0.01353  -0.1208   0.0474   1.0000
   9.000   1.5352   0.02234   0.01437  -0.1184   0.0462   1.0000
   9.250   1.5496   0.02300   0.01508  -0.1164   0.0452   1.0000
   9.500   1.5662   0.02355   0.01569  -0.1149   0.0444   1.0000
   9.750   1.5817   0.02419   0.01640  -0.1133   0.0436   1.0000
  10.000   1.5971   0.02487   0.01713  -0.1118   0.0425   1.0000
  10.250   1.6125   0.02557   0.01788  -0.1104   0.0411   1.0000
  10.500   1.6269   0.02636   0.01870  -0.1089   0.0396   1.0000
  10.750   1.6400   0.02726   0.01964  -0.1073   0.0381   1.0000
  11.000   1.6565   0.02791   0.02038  -0.1061   0.0360   1.0000
  11.250   1.6720   0.02866   0.02114  -0.1049   0.0326   1.0000
  11.500   1.6857   0.02955   0.02202  -0.1036   0.0238   1.0000
  11.750   1.6909   0.03116   0.02353  -0.1014   0.0177   1.0000
  12.000   1.6955   0.03287   0.02530  -0.0993   0.0158   1.0000
  12.250   1.7011   0.03455   0.02705  -0.0974   0.0147   1.0000
  12.500   1.7065   0.03627   0.02886  -0.0957   0.0139   1.0000
  12.750   1.7105   0.03817   0.03085  -0.0939   0.0132   1.0000
  13.000   1.7132   0.04026   0.03303  -0.0922   0.0127   1.0000
  13.250   1.7143   0.04256   0.03543  -0.0906   0.0122   1.0000
  13.500   1.7156   0.04491   0.03788  -0.0891   0.0118   1.0000
  13.750   1.7176   0.04726   0.04035  -0.0879   0.0115   1.0000
  14.000   1.7184   0.04983   0.04303  -0.0868   0.0113   1.0000
  14.250   1.7181   0.05262   0.04594  -0.0858   0.0110   1.0000
  14.500   1.7167   0.05565   0.04908  -0.0850   0.0107   1.0000
  14.750   1.7145   0.05892   0.05247  -0.0845   0.0105   1.0000
  15.000   1.7112   0.06246   0.05612  -0.0841   0.0102   1.0000
  15.250   1.7066   0.06627   0.06005  -0.0840   0.0100   1.0000
  15.500   1.7005   0.07040   0.06430  -0.0840   0.0098   1.0000
  15.750   1.6931   0.07485   0.06886  -0.0843   0.0096   1.0000
  16.000   1.6837   0.07968   0.07381  -0.0849   0.0094   1.0000
  16.250   1.6718   0.08494   0.07920  -0.0856   0.0092   1.0000
  16.500   1.6621   0.08994   0.08432  -0.0864   0.0091   1.0000
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