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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 100,000
Max Cl/Cd: 64.03 at α=4.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe198-il-100000-n5.txt
Download as CSV file: xf-goe198-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2709   0.12208   0.11707  -0.0343   1.0000   0.0401
  -9.500  -0.2744   0.12037   0.11542  -0.0322   1.0000   0.0405
  -9.250  -0.2796   0.11899   0.11409  -0.0300   1.0000   0.0410
  -9.000  -0.2739   0.11647   0.11159  -0.0307   0.9977   0.0417
  -8.750  -0.2604   0.11324   0.10835  -0.0338   0.9939   0.0428
  -8.500  -0.2482   0.11025   0.10536  -0.0368   0.9892   0.0443
  -8.250  -0.2355   0.10785   0.10295  -0.0420   0.9838   0.0458
  -8.000  -0.2280   0.10622   0.10132  -0.0473   0.9754   0.0462
  -7.750  -0.2109   0.10249   0.09760  -0.0519   0.9705   0.0465
  -7.500  -0.1952   0.09797   0.09307  -0.0516   0.9670   0.0471
  -7.250  -0.1755   0.09424   0.08932  -0.0547   0.9626   0.0481
  -7.000  -0.1528   0.09064   0.08570  -0.0595   0.9588   0.0494
  -6.750  -0.1371   0.08777   0.08281  -0.0629   0.9513   0.0508
  -6.500  -0.1080   0.08481   0.07979  -0.0723   0.9456   0.0532
  -6.250  -0.0814   0.08216   0.07708  -0.0816   0.9370   0.0539
  -6.000  -0.0659   0.07798   0.07291  -0.0805   0.9330   0.0546
  -5.750  -0.0412   0.07445   0.06934  -0.0837   0.9293   0.0558
  -5.250   0.0042   0.06885   0.06367  -0.0911   0.9165   0.0591
  -5.000   0.0522   0.06622   0.06082  -0.1036   0.9115   0.0616
  -4.750   0.0761   0.06316   0.05771  -0.1069   0.9048   0.0621
  -4.500   0.0913   0.05997   0.05457  -0.1060   0.9006   0.0633
  -4.250   0.1185   0.05726   0.05180  -0.1087   0.8971   0.0658
  -4.000   0.1461   0.05507   0.04952  -0.1123   0.8895   0.0687
  -3.750   0.2059   0.05282   0.04686  -0.1235   0.8850   0.0710
  -3.500   0.2249   0.04942   0.04353  -0.1237   0.8804   0.0717
  -3.250   0.2451   0.04712   0.04123  -0.1241   0.8730   0.0729
  -3.000   0.2759   0.04477   0.03880  -0.1265   0.8685   0.0748
  -2.750   0.3074   0.04274   0.03665  -0.1290   0.8620   0.0773
  -2.500   0.3569   0.04112   0.03457  -0.1347   0.8555   0.0819
  -2.250   0.3795   0.03828   0.03183  -0.1351   0.8502   0.0841
  -2.000   0.4056   0.03664   0.03012  -0.1358   0.8407   0.0873
  -1.750   0.4587   0.03309   0.02586  -0.1401   0.8356   0.0616
  -1.250   0.5224   0.02879   0.02112  -0.1422   0.8197   0.0532
  -1.000   0.5503   0.02744   0.01965  -0.1426   0.8095   0.0524
  -0.750   0.5829   0.02593   0.01788  -0.1433   0.8025   0.0517
  -0.500   0.6132   0.02471   0.01636  -0.1435   0.7921   0.0529
  -0.250   0.6442   0.02355   0.01484  -0.1437   0.7828   0.0537
   0.000   0.6741   0.02249   0.01356  -0.1437   0.7734   0.0536
   0.250   0.7022   0.02163   0.01253  -0.1435   0.7616   0.0538
   0.500   0.7305   0.02083   0.01161  -0.1432   0.7499   0.0544
   0.750   0.7593   0.02012   0.01078  -0.1429   0.7386   0.0553
   1.000   0.7867   0.01960   0.01020  -0.1426   0.7259   0.0567
   1.250   0.8138   0.01921   0.00973  -0.1421   0.7134   0.0602
   1.500   0.8414   0.01880   0.00927  -0.1417   0.7007   0.0635
   1.750   0.8689   0.01841   0.00884  -0.1413   0.6876   0.0665
   2.000   0.8959   0.01809   0.00840  -0.1407   0.6738   0.0706
   2.250   0.9229   0.01782   0.00809  -0.1402   0.6593   0.0773
   2.500   0.9499   0.01766   0.00786  -0.1398   0.6445   0.0929
   2.750   0.9772   0.01750   0.00770  -0.1394   0.6297   0.1210
   3.000   0.9973   0.01604   0.00773  -0.1378   0.6142   1.0000
   3.250   1.0234   0.01625   0.00767  -0.1371   0.5964   1.0000
   3.500   1.0488   0.01650   0.00770  -0.1364   0.5767   1.0000
   3.750   1.0735   0.01681   0.00781  -0.1356   0.5556   1.0000
   4.000   1.0980   0.01717   0.00797  -0.1348   0.5352   1.0000
   4.250   1.1224   0.01753   0.00822  -0.1341   0.5172   1.0000
   4.500   1.1468   0.01791   0.00849  -0.1334   0.5006   1.0000
   4.750   1.1709   0.01829   0.00881  -0.1328   0.4841   1.0000
   5.000   1.1944   0.01868   0.00914  -0.1320   0.4661   1.0000
   5.250   1.2174   0.01909   0.00950  -0.1312   0.4470   1.0000
   5.500   1.2401   0.01951   0.00987  -0.1303   0.4281   1.0000
   5.750   1.2626   0.01995   0.01026  -0.1294   0.4107   1.0000
   6.000   1.2844   0.02042   0.01069  -0.1285   0.3939   1.0000
   6.250   1.3053   0.02096   0.01114  -0.1274   0.3771   1.0000
   6.500   1.3257   0.02153   0.01163  -0.1262   0.3625   1.0000
   6.750   1.3458   0.02214   0.01217  -0.1250   0.3500   1.0000
   7.000   1.3664   0.02271   0.01277  -0.1239   0.3386   1.0000
   7.250   1.3867   0.02331   0.01338  -0.1228   0.3288   1.0000
   7.500   1.4063   0.02393   0.01402  -0.1216   0.3195   1.0000
   7.750   1.4262   0.02452   0.01471  -0.1205   0.3103   1.0000
   8.000   1.4436   0.02521   0.01541  -0.1189   0.2993   1.0000
   8.250   1.4620   0.02582   0.01613  -0.1176   0.2885   1.0000
   8.500   1.4795   0.02646   0.01688  -0.1161   0.2785   1.0000
   8.750   1.4947   0.02717   0.01766  -0.1142   0.2668   1.0000
   9.000   1.5087   0.02789   0.01850  -0.1123   0.2507   1.0000
   9.250   1.5198   0.02867   0.01937  -0.1098   0.2296   1.0000
   9.500   1.5283   0.02967   0.02037  -0.1072   0.2048   1.0000
   9.750   1.5313   0.03111   0.02166  -0.1041   0.1745   1.0000
  10.000   1.5325   0.03288   0.02328  -0.1011   0.1478   1.0000
  10.250   1.5340   0.03478   0.02511  -0.0984   0.1241   1.0000
  10.500   1.5352   0.03680   0.02706  -0.0958   0.1079   1.0000
  10.750   1.5367   0.03884   0.02911  -0.0935   0.0976   1.0000
  11.000   1.5380   0.04096   0.03126  -0.0913   0.0906   1.0000
  11.250   1.5369   0.04335   0.03368  -0.0891   0.0850   1.0000
  11.500   1.5365   0.04574   0.03617  -0.0872   0.0807   1.0000
  11.750   1.5342   0.04840   0.03892  -0.0854   0.0771   1.0000
  12.000   1.5288   0.05146   0.04209  -0.0838   0.0744   1.0000
  12.250   1.5250   0.05448   0.04524  -0.0824   0.0719   1.0000
  12.500   1.5209   0.05764   0.04857  -0.0813   0.0695   1.0000
  12.750   1.5144   0.06120   0.05226  -0.0804   0.0673   1.0000
  13.000   1.5049   0.06522   0.05638  -0.0797   0.0652   1.0000
  13.250   1.4961   0.06929   0.06053  -0.0792   0.0632   1.0000
  13.500   1.4931   0.07284   0.06428  -0.0789   0.0610   1.0000
  13.750   1.4886   0.07664   0.06823  -0.0788   0.0588   1.0000
  14.000   1.4833   0.08056   0.07225  -0.0788   0.0567   1.0000
  14.250   1.4785   0.08417   0.07589  -0.0784   0.0546   1.0000
  14.500   1.4768   0.08780   0.07973  -0.0785   0.0521   1.0000
  14.750   1.4742   0.09159   0.08369  -0.0788   0.0493   1.0000
  15.000   1.4715   0.09522   0.08738  -0.0790   0.0467   1.0000
  15.250   1.4690   0.09902   0.09133  -0.0794   0.0440   1.0000
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