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GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 198 (L.F.G. 5294) AIRFOIL (goe198-il)
Reynolds number: 100,000
Max Cl/Cd: 64.55 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe198-il-100000.txt
Download as CSV file: xf-goe198-il-100000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3212   0.11266   0.10811  -0.0178   1.0000   0.0559
  -7.500  -0.3337   0.11211   0.10763  -0.0154   1.0000   0.0565
  -7.250  -0.3463   0.11172   0.10731  -0.0137   1.0000   0.0569
  -7.000  -0.3541   0.11140   0.10705  -0.0146   1.0000   0.0574
  -6.750  -0.3570   0.11128   0.10697  -0.0183   1.0000   0.0577
  -6.500  -0.3519   0.11039   0.10610  -0.0238   1.0000   0.0580
  -6.250  -0.3544   0.10468   0.10046  -0.0166   1.0000   0.0586
  -6.000  -0.3497   0.10088   0.09668  -0.0141   0.9992   0.0595
  -5.750  -0.3245   0.09672   0.09249  -0.0184   0.9945   0.0613
  -5.500  -0.2972   0.09298   0.08871  -0.0243   0.9885   0.0633
  -5.250  -0.2593   0.08928   0.08495  -0.0339   0.9830   0.0662
  -5.000  -0.1925   0.08723   0.08266  -0.0556   0.9737   0.0683
  -4.750  -0.1796   0.08153   0.07702  -0.0536   0.9702   0.0692
  -4.500  -0.1637   0.07799   0.07349  -0.0540   0.9628   0.0706
  -4.250  -0.1276   0.07438   0.06983  -0.0598   0.9575   0.0739
  -4.000  -0.0482   0.07306   0.06811  -0.0798   0.9480   0.0797
  -3.750  -0.0324   0.06770   0.06286  -0.0793   0.9435   0.0808
  -3.500  -0.0091   0.06443   0.05960  -0.0808   0.9369   0.0829
  -3.250   0.0290   0.06151   0.05660  -0.0861   0.9298   0.0869
  -3.000   0.1013   0.05820   0.05299  -0.0997   0.9259   0.0934
  -2.750   0.1196   0.05550   0.05033  -0.0998   0.9159   0.0958
  -2.500   0.1879   0.05318   0.04766  -0.1108   0.9114   0.1070
  -2.250   0.2082   0.05022   0.04481  -0.1111   0.9022   0.1106
  -2.000   0.2690   0.04769   0.04199  -0.1195   0.8969   0.1228
  -1.750   0.3064   0.04517   0.03947  -0.1226   0.8893   0.1310
  -1.500   0.3563   0.04262   0.03678  -0.1281   0.8824   0.1445
  -1.250   0.4195   0.04011   0.03402  -0.1359   0.8794   0.1703
  -1.000   0.4493   0.03838   0.03229  -0.1371   0.8686   0.1886
  -0.750   0.4967   0.03632   0.03015  -0.1414   0.8643   0.2350
  -0.500   0.5229   0.03464   0.02854  -0.1416   0.8536   0.2840
   0.500   0.7053   0.02817   0.02052  -0.1505   0.8211   0.1455
   0.750   0.7475   0.02671   0.01853  -0.1510   0.8153   0.1192
   1.000   0.7751   0.02584   0.01754  -0.1504   0.8035   0.1177
   1.250   0.8123   0.02444   0.01596  -0.1507   0.7981   0.1140
   1.500   0.8381   0.02382   0.01525  -0.1497   0.7855   0.1131
   1.750   0.8660   0.02317   0.01454  -0.1489   0.7747   0.1152
   2.000   0.8985   0.02215   0.01348  -0.1486   0.7675   0.1241
   2.250   0.9240   0.02165   0.01297  -0.1474   0.7550   0.1356
   2.500   0.9522   0.02093   0.01232  -0.1466   0.7437   0.1622
   2.750   0.9786   0.01873   0.01148  -0.1449   0.7354   1.0000
   3.000   1.0051   0.01867   0.01117  -0.1439   0.7216   1.0000
   3.250   1.0321   0.01855   0.01090  -0.1430   0.7073   1.0000
   3.500   1.0593   0.01837   0.01059  -0.1421   0.6919   1.0000
   3.750   1.0866   0.01818   0.01026  -0.1412   0.6749   1.0000
   4.000   1.1139   0.01802   0.00993  -0.1402   0.6565   1.0000
   4.250   1.1383   0.01812   0.00996  -0.1391   0.6346   1.0000
   4.500   1.1639   0.01824   0.00994  -0.1381   0.6138   1.0000
   4.750   1.1900   0.01844   0.00996  -0.1373   0.5939   1.0000
   5.000   1.2141   0.01881   0.01022  -0.1364   0.5720   1.0000
   5.250   1.2385   0.01923   0.01053  -0.1355   0.5512   1.0000
   5.500   1.2629   0.01969   0.01086  -0.1347   0.5320   1.0000
   5.750   1.2873   0.02021   0.01130  -0.1340   0.5149   1.0000
   6.000   1.3111   0.02072   0.01178  -0.1332   0.4985   1.0000
   6.250   1.3342   0.02121   0.01225  -0.1323   0.4826   1.0000
   6.500   1.3569   0.02168   0.01273  -0.1314   0.4675   1.0000
   6.750   1.3795   0.02214   0.01321  -0.1305   0.4534   1.0000
   7.000   1.4020   0.02259   0.01372  -0.1296   0.4405   1.0000
   7.250   1.4237   0.02301   0.01416  -0.1286   0.4272   1.0000
   7.500   1.4453   0.02344   0.01460  -0.1275   0.4145   1.0000
   7.750   1.4664   0.02393   0.01517  -0.1264   0.4026   1.0000
   8.000   1.4873   0.02446   0.01581  -0.1253   0.3912   1.0000
   8.250   1.5079   0.02500   0.01641  -0.1241   0.3801   1.0000
   8.500   1.5268   0.02556   0.01698  -0.1227   0.3670   1.0000
   8.750   1.5441   0.02617   0.01761  -0.1210   0.3527   1.0000
   9.000   1.5603   0.02684   0.01837  -0.1192   0.3385   1.0000
   9.250   1.5741   0.02755   0.01918  -0.1169   0.3231   1.0000
   9.500   1.5845   0.02833   0.02002  -0.1142   0.3056   1.0000
   9.750   1.5895   0.02914   0.02104  -0.1107   0.2842   1.0000
  10.000   1.5878   0.03011   0.02208  -0.1062   0.2587   1.0000
  10.250   1.5825   0.03147   0.02346  -0.1016   0.2195   1.0000
  10.500   1.5727   0.03366   0.02537  -0.0972   0.1807   1.0000
  10.750   1.5637   0.03626   0.02771  -0.0935   0.1581   1.0000
  11.000   1.5581   0.03884   0.03015  -0.0904   0.1432   1.0000
  11.250   1.5553   0.04130   0.03259  -0.0878   0.1314   1.0000
  11.500   1.5543   0.04368   0.03502  -0.0855   0.1219   1.0000
  11.750   1.5505   0.04637   0.03768  -0.0832   0.1154   1.0000
  12.000   1.5506   0.04882   0.04024  -0.0813   0.1089   1.0000
  12.250   1.5461   0.05173   0.04309  -0.0793   0.1038   1.0000
  12.500   1.5464   0.05431   0.04586  -0.0777   0.0979   1.0000
  12.750   1.5433   0.05723   0.04870  -0.0759   0.0925   1.0000
  13.000   1.5437   0.05998   0.05159  -0.0743   0.0867   1.0000
  13.250   1.5485   0.06235   0.05375  -0.0722   0.0798   1.0000
  13.500   1.5503   0.06518   0.05673  -0.0706   0.0740   1.0000
  13.750   1.5727   0.06698   0.05839  -0.0684   0.0672   1.0000
  14.000   1.5847   0.06953   0.06112  -0.0669   0.0633   1.0000
  14.250   1.6214   0.07229   0.06379  -0.0660   0.0581   1.0000
  14.500   1.6116   0.07580   0.06764  -0.0644   0.0569   1.0000
  14.750   1.6041   0.07954   0.07170  -0.0632   0.0556   1.0000
  15.000   1.5973   0.08352   0.07597  -0.0623   0.0545   1.0000
  15.250   1.5892   0.08775   0.08047  -0.0616   0.0537   1.0000
  15.500   1.5785   0.09227   0.08526  -0.0613   0.0532   1.0000
  15.750   1.5652   0.09713   0.09040  -0.0615   0.0527   1.0000
  16.000   1.5486   0.10247   0.09602  -0.0623   0.0525   1.0000
  16.250   1.5284   0.10844   0.10227  -0.0639   0.0525   1.0000
  16.500   1.5041   0.11536   0.10949  -0.0667   0.0527   1.0000
  16.750   1.4762   0.12347   0.11792  -0.0709   0.0532   1.0000
  17.000   1.4452   0.13297   0.12772  -0.0767   0.0539   1.0000
  17.250   1.4120   0.14393   0.13896  -0.0841   0.0548   1.0000
  17.500   1.3769   0.15674   0.15200  -0.0933   0.0561   1.0000
  17.750   1.3429   0.17098   0.16636  -0.1035   0.0575   1.0000
  18.000   1.3216   0.18298   0.17842  -0.1112   0.0586   1.0000
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