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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 500,000
Max Cl/Cd: 112.31 at α=3.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe198-il-500000.txt
Download as CSV file: xf-goe198-il-500000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.1610   0.09064   0.08816  -0.0569   0.9247   0.0223
  -7.750  -0.1520   0.08814   0.08566  -0.0582   0.9186   0.0227
  -7.500  -0.1436   0.08570   0.08320  -0.0594   0.9129   0.0232
  -7.250  -0.1336   0.08320   0.08068  -0.0614   0.9080   0.0239
  -7.000  -0.1174   0.08025   0.07771  -0.0661   0.9023   0.0249
  -6.750  -0.0931   0.07698   0.07437  -0.0764   0.8964   0.0252
  -6.500  -0.0683   0.07342   0.07075  -0.0837   0.8917   0.0252
  -6.250  -0.0554   0.06973   0.06707  -0.0843   0.8869   0.0254
  -6.000  -0.0421   0.06698   0.06430  -0.0839   0.8823   0.0256
  -5.750  -0.0249   0.06443   0.06171  -0.0852   0.8781   0.0258
  -5.500  -0.0041   0.06183   0.05910  -0.0878   0.8730   0.0262
  -5.250   0.0190   0.05920   0.05644  -0.0910   0.8680   0.0268
  -5.000   0.0447   0.05643   0.05360  -0.0948   0.8637   0.0276
  -4.750   0.0742   0.05342   0.05053  -0.0995   0.8592   0.0287
  -4.500   0.1338   0.04895   0.04583  -0.1125   0.8542   0.0298
  -4.250   0.1547   0.04541   0.04226  -0.1143   0.8498   0.0301
  -4.000   0.1763   0.04328   0.04008  -0.1151   0.8460   0.0305
  -3.750   0.2024   0.04118   0.03796  -0.1169   0.8412   0.0309
  -3.500   0.2315   0.03907   0.03580  -0.1193   0.8364   0.0317
  -3.250   0.2634   0.03682   0.03345  -0.1221   0.8319   0.0329
  -3.000   0.3171   0.03360   0.02987  -0.1282   0.8272   0.0353
  -2.750   0.3433   0.03045   0.02669  -0.1302   0.8212   0.0359
  -2.500   0.3698   0.02896   0.02514  -0.1312   0.8157   0.0365
  -2.250   0.3993   0.02744   0.02356  -0.1325   0.8096   0.0376
  -2.000   0.4326   0.02567   0.02165  -0.1342   0.8032   0.0399
  -1.750   0.4718   0.02284   0.01846  -0.1365   0.7977   0.0426
  -1.500   0.4999   0.02177   0.01740  -0.1374   0.7895   0.0435
  -1.250   0.5295   0.02075   0.01626  -0.1381   0.7826   0.0457
  -1.000   0.5661   0.01884   0.01400  -0.1394   0.7739   0.0502
  -0.750   0.5945   0.01786   0.01297  -0.1400   0.7640   0.0513
  -0.500   0.6239   0.01706   0.01206  -0.1405   0.7522   0.0537
  -0.250   0.6569   0.01596   0.01062  -0.1410   0.7398   0.0593
   0.000   0.6856   0.01512   0.00972  -0.1415   0.7247   0.0610
   0.250   0.7224   0.01215   0.00598  -0.1418   0.7089   0.0420
   0.500   0.7510   0.01149   0.00509  -0.1418   0.6857   0.0422
   0.750   0.7786   0.01126   0.00466  -0.1416   0.6571   0.0417
   1.000   0.8067   0.01079   0.00402  -0.1416   0.6317   0.0415
   1.500   0.8623   0.01032   0.00331  -0.1415   0.5902   0.0432
   1.750   0.8900   0.01032   0.00324  -0.1415   0.5726   0.0448
   2.000   0.9175   0.01037   0.00323  -0.1414   0.5567   0.0469
   2.250   0.9450   0.01044   0.00323  -0.1414   0.5421   0.0508
   2.500   0.9724   0.01056   0.00331  -0.1413   0.5277   0.0564
   3.000   1.0272   0.01074   0.00347  -0.1412   0.4972   0.0989
   3.250   1.0543   0.01086   0.00359  -0.1412   0.4805   0.1201
   3.500   1.0748   0.00957   0.00386  -0.1400   0.4632   1.0000
   3.750   1.1008   0.00987   0.00397  -0.1397   0.4318   1.0000
   4.000   1.1253   0.01032   0.00416  -0.1392   0.3883   1.0000
   4.500   1.1737   0.01127   0.00472  -0.1382   0.3355   1.0000
   4.750   1.1987   0.01165   0.00499  -0.1378   0.3209   1.0000
   5.000   1.2239   0.01198   0.00526  -0.1375   0.3079   1.0000
   5.250   1.2494   0.01227   0.00549  -0.1372   0.2960   1.0000
   5.500   1.2747   0.01258   0.00574  -0.1368   0.2846   1.0000
   5.750   1.2996   0.01290   0.00601  -0.1364   0.2728   1.0000
   6.000   1.3244   0.01322   0.00627  -0.1360   0.2570   1.0000
   6.250   1.3486   0.01358   0.00655  -0.1355   0.2368   1.0000
   6.500   1.3685   0.01435   0.00702  -0.1344   0.1883   1.0000
   6.750   1.3835   0.01557   0.00787  -0.1325   0.1310   1.0000
   7.000   1.3965   0.01691   0.00885  -0.1304   0.0760   1.0000
   7.250   1.4174   0.01746   0.00937  -0.1293   0.0700   1.0000
   7.500   1.4386   0.01795   0.00989  -0.1283   0.0676   1.0000
   7.750   1.4586   0.01850   0.01046  -0.1271   0.0655   1.0000
   8.000   1.4774   0.01909   0.01110  -0.1258   0.0638   1.0000
   8.250   1.4954   0.01970   0.01174  -0.1243   0.0623   1.0000
   8.500   1.5119   0.02036   0.01245  -0.1225   0.0609   1.0000
   8.750   1.5260   0.02112   0.01327  -0.1204   0.0593   1.0000
   9.000   1.5396   0.02176   0.01398  -0.1181   0.0584   1.0000
   9.250   1.5534   0.02243   0.01472  -0.1160   0.0575   1.0000
   9.500   1.5664   0.02319   0.01555  -0.1139   0.0566   1.0000
   9.750   1.5788   0.02403   0.01647  -0.1118   0.0556   1.0000
  10.000   1.5902   0.02499   0.01749  -0.1097   0.0542   1.0000
  10.250   1.5998   0.02611   0.01868  -0.1076   0.0525   1.0000
  10.500   1.6050   0.02760   0.02023  -0.1050   0.0507   1.0000
  10.750   1.6060   0.02948   0.02220  -0.1022   0.0491   1.0000
  11.000   1.6252   0.02997   0.02277  -0.1014   0.0479   1.0000
  11.250   1.6414   0.03069   0.02357  -0.1003   0.0460   1.0000
  11.500   1.6559   0.03156   0.02450  -0.0992   0.0436   1.0000
  11.750   1.6621   0.03315   0.02612  -0.0973   0.0411   1.0000
  12.000   1.6881   0.03308   0.02610  -0.0973   0.0370   1.0000
  12.250   1.7081   0.03350   0.02650  -0.0967   0.0315   1.0000
  12.500   1.7213   0.03452   0.02747  -0.0955   0.0259   1.0000
  13.000   1.7305   0.03817   0.03117  -0.0920   0.0213   1.0000
  13.250   1.7320   0.04038   0.03345  -0.0903   0.0201   1.0000
  13.500   1.7304   0.04296   0.03610  -0.0885   0.0192   1.0000
  13.750   1.7267   0.04586   0.03910  -0.0868   0.0185   1.0000
  14.000   1.7252   0.04864   0.04202  -0.0855   0.0181   1.0000
  14.250   1.7223   0.05170   0.04520  -0.0844   0.0176   1.0000
  14.500   1.7180   0.05505   0.04868  -0.0835   0.0172   1.0000
  14.750   1.7128   0.05870   0.05245  -0.0829   0.0168   1.0000
  15.000   1.7062   0.06268   0.05654  -0.0826   0.0164   1.0000
  15.250   1.6974   0.06710   0.06107  -0.0825   0.0161   1.0000
  15.500   1.6867   0.07192   0.06601  -0.0827   0.0158   1.0000
  15.750   1.6739   0.07717   0.07137  -0.0831   0.0155   1.0000
  16.000   1.6599   0.08268   0.07700  -0.0837   0.0153   1.0000
  16.250   1.6484   0.08784   0.08228  -0.0844   0.0151   1.0000
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