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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 1,000,000
Max Cl/Cd: 116.99 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe198-il-1000000.txt
Download as CSV file: xf-goe198-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.2260   0.10510   0.10306  -0.0421   0.8935   0.0166
  -9.000  -0.2171   0.10213   0.10010  -0.0438   0.8903   0.0174
  -8.750  -0.2096   0.09894   0.09690  -0.0467   0.8862   0.0177
  -8.500  -0.1201   0.08148   0.07948  -0.0573   0.8687   0.0179
  -8.250  -0.1108   0.07820   0.07618  -0.0569   0.8652   0.0180
  -8.000  -0.1027   0.07542   0.07338  -0.0573   0.8612   0.0182
  -7.750  -0.1807   0.08642   0.08435  -0.0546   0.8704   0.0180
  -7.500  -0.1687   0.08371   0.08162  -0.0557   0.8665   0.0181
  -7.250  -0.1554   0.08117   0.07905  -0.0575   0.8619   0.0182
  -7.000  -0.1403   0.07853   0.07641  -0.0601   0.8579   0.0184
  -6.750  -0.1238   0.07586   0.07373  -0.0631   0.8532   0.0187
  -6.500  -0.1060   0.07314   0.07099  -0.0664   0.8489   0.0192
  -6.250  -0.0862   0.07023   0.06803  -0.0702   0.8449   0.0198
  -6.000  -0.0565   0.06632   0.06410  -0.0781   0.8407   0.0211
  -5.750  -0.0239   0.06223   0.05994  -0.0867   0.8363   0.0212
  -5.500   0.0048   0.05859   0.05623  -0.0923   0.8322   0.0213
  -5.250   0.0329   0.05423   0.05181  -0.0977   0.8285   0.0214
  -5.000   0.0516   0.05159   0.04916  -0.0988   0.8247   0.0216
  -4.750   0.0758   0.04930   0.04686  -0.1010   0.8206   0.0218
  -4.500   0.1026   0.04700   0.04450  -0.1039   0.8165   0.0221
  -4.250   0.1319   0.04461   0.04205  -0.1072   0.8122   0.0226
  -4.000   0.1634   0.04204   0.03943  -0.1108   0.8068   0.0233
  -3.750   0.2101   0.03832   0.03553  -0.1175   0.8014   0.0251
  -3.500   0.2468   0.03529   0.03237  -0.1214   0.7962   0.0252
  -3.250   0.2819   0.03237   0.02933  -0.1246   0.7905   0.0252
  -3.000   0.3116   0.02901   0.02585  -0.1275   0.7847   0.0257
  -2.750   0.3408   0.02752   0.02430  -0.1290   0.7788   0.0260
  -2.500   0.3711   0.02602   0.02272  -0.1305   0.7716   0.0265
  -2.250   0.4029   0.02435   0.02093  -0.1322   0.7639   0.0274
  -2.000   0.4445   0.02149   0.01776  -0.1342   0.7550   0.0298
  -1.750   0.4780   0.01841   0.01443  -0.1366   0.7457   0.0305
  -1.500   0.5074   0.01754   0.01345  -0.1374   0.7342   0.0310
  -1.250   0.5373   0.01667   0.01245  -0.1381   0.7205   0.0316
  -1.000   0.5678   0.01575   0.01135  -0.1388   0.7042   0.0330
  -0.750   0.6004   0.01489   0.01012  -0.1389   0.6822   0.0353
  -0.250   0.6656   0.01011   0.00430  -0.1411   0.6207   0.0307
   0.000   0.6937   0.00990   0.00385  -0.1411   0.5874   0.0305
   0.250   0.7220   0.00970   0.00350  -0.1413   0.5666   0.0305
   0.500   0.7506   0.00949   0.00319  -0.1414   0.5518   0.0308
   0.750   0.7791   0.00936   0.00301  -0.1416   0.5390   0.0315
   1.000   0.8075   0.00928   0.00286  -0.1417   0.5268   0.0319
   1.250   0.8361   0.00921   0.00274  -0.1419   0.5152   0.0325
   1.500   0.8646   0.00917   0.00266  -0.1420   0.5035   0.0335
   1.750   0.8929   0.00918   0.00262  -0.1421   0.4903   0.0344
   2.000   0.9210   0.00924   0.00261  -0.1422   0.4753   0.0352
   2.250   0.9492   0.00926   0.00257  -0.1423   0.4579   0.0367
   2.500   0.9766   0.00941   0.00262  -0.1423   0.4308   0.0390
   2.750   1.0024   0.00978   0.00275  -0.1421   0.3798   0.0439
   3.000   1.0282   0.01014   0.00300  -0.1418   0.3448   0.0703
   3.250   1.0545   0.01042   0.00319  -0.1417   0.3253   0.0823
   3.500   1.0810   0.01067   0.00337  -0.1416   0.3082   0.0907
   3.750   1.1079   0.01085   0.00351  -0.1415   0.2952   0.0999
   4.000   1.1354   0.01087   0.00376  -0.1417   0.2826   0.2608
   4.250   1.1570   0.00989   0.00405  -0.1408   0.2696   1.0000
   4.500   1.1828   0.01022   0.00423  -0.1405   0.2470   1.0000
   4.750   1.2041   0.01108   0.00466  -0.1397   0.1799   1.0000
   5.000   1.2186   0.01272   0.00567  -0.1378   0.0688   1.0000
   5.250   1.2436   0.01307   0.00596  -0.1374   0.0633   1.0000
   5.500   1.2689   0.01337   0.00623  -0.1370   0.0600   1.0000
   5.750   1.2943   0.01364   0.00650  -0.1366   0.0585   1.0000
   6.000   1.3194   0.01392   0.00680  -0.1362   0.0578   1.0000
   6.250   1.3442   0.01422   0.00711  -0.1358   0.0569   1.0000
   6.500   1.3685   0.01455   0.00745  -0.1353   0.0558   1.0000
   6.750   1.3923   0.01491   0.00783  -0.1347   0.0546   1.0000
   7.000   1.4156   0.01531   0.00824  -0.1341   0.0532   1.0000
   7.250   1.4384   0.01572   0.00866  -0.1333   0.0520   1.0000
   7.500   1.4606   0.01618   0.00914  -0.1325   0.0508   1.0000
   7.750   1.4814   0.01671   0.00973  -0.1314   0.0495   1.0000
   8.000   1.5030   0.01714   0.01020  -0.1305   0.0490   1.0000
   8.250   1.5249   0.01750   0.01058  -0.1296   0.0487   1.0000
   8.500   1.5468   0.01783   0.01092  -0.1288   0.0480   1.0000
   8.750   1.5678   0.01819   0.01132  -0.1278   0.0472   1.0000
   9.000   1.5879   0.01858   0.01174  -0.1267   0.0462   1.0000
   9.250   1.6072   0.01901   0.01218  -0.1254   0.0451   1.0000
   9.500   1.6257   0.01944   0.01264  -0.1240   0.0441   1.0000
   9.750   1.6416   0.01996   0.01318  -0.1222   0.0428   1.0000
  10.000   1.6524   0.02071   0.01398  -0.1195   0.0413   1.0000
  10.250   1.6700   0.02111   0.01441  -0.1180   0.0400   1.0000
  10.500   1.6918   0.02127   0.01457  -0.1173   0.0384   1.0000
  10.750   1.7113   0.02158   0.01485  -0.1162   0.0351   1.0000
  11.000   1.7283   0.02207   0.01531  -0.1148   0.0298   1.0000
  11.250   1.7371   0.02314   0.01623  -0.1124   0.0193   1.0000
  11.500   1.7458   0.02428   0.01740  -0.1101   0.0170   1.0000
  11.750   1.7536   0.02554   0.01869  -0.1078   0.0156   1.0000
  12.000   1.7628   0.02673   0.01996  -0.1057   0.0148   1.0000
  12.250   1.7720   0.02796   0.02126  -0.1038   0.0143   1.0000
  12.500   1.7794   0.02934   0.02272  -0.1018   0.0137   1.0000
  12.750   1.7850   0.03091   0.02435  -0.0997   0.0132   1.0000
  13.000   1.7881   0.03275   0.02627  -0.0975   0.0127   1.0000
  13.250   1.7874   0.03497   0.02859  -0.0952   0.0121   1.0000
  13.500   1.7933   0.03666   0.03036  -0.0936   0.0119   1.0000
  13.750   1.7975   0.03856   0.03235  -0.0919   0.0117   1.0000
  14.000   1.8000   0.04068   0.03455  -0.0904   0.0115   1.0000
  14.250   1.8012   0.04297   0.03694  -0.0888   0.0112   1.0000
  14.500   1.8008   0.04551   0.03958  -0.0874   0.0110   1.0000
  14.750   1.7996   0.04827   0.04243  -0.0862   0.0108   1.0000
  15.000   1.7974   0.05126   0.04552  -0.0852   0.0106   1.0000
  15.250   1.7935   0.05457   0.04893  -0.0844   0.0104   1.0000
  15.500   1.7875   0.05832   0.05278  -0.0838   0.0102   1.0000
  15.750   1.7790   0.06254   0.05712  -0.0835   0.0100   1.0000
  16.000   1.7683   0.06722   0.06191  -0.0834   0.0099   1.0000
  16.250   1.7538   0.07259   0.06741  -0.0837   0.0098   1.0000
  16.500   1.7370   0.07846   0.07343  -0.0843   0.0096   1.0000
  16.750   1.7261   0.08352   0.07860  -0.0849   0.0095   1.0000
  17.000   1.7185   0.08813   0.08332  -0.0856   0.0095   1.0000
  17.250   1.7103   0.09288   0.08818  -0.0864   0.0094   1.0000
  17.500   1.7017   0.09775   0.09316  -0.0874   0.0093   1.0000
  17.750   1.6923   0.10280   0.09832  -0.0885   0.0092   1.0000
  18.000   1.6829   0.10788   0.10350  -0.0898   0.0092   1.0000
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