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GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 498 AIRFOIL (goe498-il)
Reynolds number: 100,000
Max Cl/Cd: 49.67 at α=8.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe498-il-100000.txt
Download as CSV file: xf-goe498-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 498 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2738   0.11129   0.10648  -0.0412   0.9822   0.1720
  -8.500  -0.2455   0.10805   0.10321  -0.0433   0.9764   0.1762
  -8.250  -0.2688   0.10591   0.10110  -0.0527   0.9657   0.1849
  -8.000  -0.2516   0.10110   0.09629  -0.0549   0.9588   0.1866
  -7.750  -0.3620   0.07248   0.06751  -0.0806   0.9403   0.1272
  -7.500  -0.3609   0.06660   0.06157  -0.0845   0.9303   0.1262
  -7.250  -0.3727   0.05036   0.04456  -0.1015   0.9220   0.1235
  -7.000  -0.3701   0.04424   0.03777  -0.1048   0.9111   0.1245
  -6.750  -0.3383   0.03958   0.03229  -0.1101   0.9061   0.1282
  -6.500  -0.3141   0.03905   0.03191  -0.1098   0.8985   0.1315
  -6.250  -0.2851   0.03749   0.03010  -0.1112   0.8912   0.1356
  -6.000  -0.2445   0.03525   0.02731  -0.1148   0.8870   0.1414
  -5.750  -0.2259   0.03478   0.02692  -0.1137   0.8780   0.1453
  -5.500  -0.1923   0.03374   0.02563  -0.1152   0.8717   0.1516
  -5.250  -0.1499   0.03254   0.02434  -0.1179   0.8680   0.1588
  -5.000  -0.1333   0.03222   0.02392  -0.1164   0.8580   0.1644
  -4.750  -0.0978   0.03127   0.02284  -0.1179   0.8524   0.1726
  -4.500  -0.0537   0.03047   0.02191  -0.1206   0.8490   0.1838
  -4.000  -0.0028   0.02961   0.02107  -0.1200   0.8331   0.2045
  -3.750   0.0426   0.02888   0.02042  -0.1226   0.8301   0.2232
  -3.500   0.0529   0.02915   0.02064  -0.1199   0.8188   0.2378
  -3.250   0.0918   0.02876   0.02041  -0.1214   0.8141   0.2606
  -3.000   0.1394   0.02826   0.01997  -0.1240   0.8115   0.2865
  -2.750   0.1460   0.02877   0.02047  -0.1208   0.7993   0.2992
  -2.500   0.1883   0.02831   0.02003  -0.1226   0.7954   0.3201
  -2.250   0.2383   0.02763   0.01938  -0.1256   0.7930   0.3422
  -1.750   0.2903   0.02759   0.01929  -0.1245   0.7771   0.3777
  -1.500   0.3404   0.02682   0.01864  -0.1272   0.7744   0.4025
  -1.250   0.3505   0.02729   0.01911  -0.1243   0.7628   0.4177
  -1.000   0.3954   0.02658   0.01841  -0.1262   0.7585   0.4408
  -0.750   0.4442   0.02570   0.01755  -0.1287   0.7553   0.4633
  -0.500   0.4550   0.02615   0.01811  -0.1258   0.7442   0.4757
  -0.250   0.4958   0.02557   0.01753  -0.1272   0.7392   0.4956
   0.000   0.5431   0.02482   0.01678  -0.1295   0.7357   0.5176
   0.250   0.5525   0.02541   0.01742  -0.1265   0.7245   0.5318
   0.500   0.5920   0.02492   0.01694  -0.1277   0.7191   0.5534
   0.750   0.6394   0.02419   0.01620  -0.1301   0.7154   0.5781
   1.000   0.6443   0.02490   0.01700  -0.1264   0.7033   0.5943
   1.250   0.6852   0.02432   0.01643  -0.1278   0.6981   0.6237
   1.500   0.7058   0.02447   0.01669  -0.1262   0.6898   0.6496
   1.750   0.7290   0.02444   0.01676  -0.1250   0.6815   0.6800
   2.000   0.7724   0.02373   0.01609  -0.1266   0.6767   0.7213
   2.250   0.7791   0.02421   0.01679  -0.1230   0.6655   0.7584
   2.500   0.8135   0.02337   0.01622  -0.1228   0.6592   0.8446
   2.750   0.8544   0.02337   0.01621  -0.1256   0.6494   1.0000
   3.000   0.8905   0.02330   0.01595  -0.1268   0.6407   1.0000
   3.250   0.9218   0.02339   0.01590  -0.1272   0.6323   1.0000
   3.500   0.9472   0.02357   0.01600  -0.1266   0.6224   1.0000
   3.750   0.9846   0.02345   0.01573  -0.1278   0.6151   1.0000
   4.000   1.0007   0.02394   0.01621  -0.1258   0.6044   1.0000
   4.250   1.0454   0.02359   0.01568  -0.1280   0.5981   1.0000
   4.500   1.0529   0.02435   0.01651  -0.1247   0.5866   1.0000
   4.750   1.0949   0.02405   0.01604  -0.1265   0.5798   1.0000
   5.000   1.1044   0.02477   0.01683  -0.1235   0.5689   1.0000
   5.250   1.1431   0.02458   0.01650  -0.1248   0.5617   1.0000
   5.500   1.1551   0.02524   0.01723  -0.1222   0.5514   1.0000
   5.750   1.1901   0.02516   0.01704  -0.1230   0.5436   1.0000
   6.000   1.2050   0.02575   0.01768  -0.1208   0.5340   1.0000
   6.250   1.2357   0.02579   0.01764  -0.1209   0.5257   1.0000
   6.500   1.2541   0.02631   0.01819  -0.1193   0.5167   1.0000
   6.750   1.2781   0.02660   0.01847  -0.1185   0.5084   1.0000
   7.000   1.3048   0.02694   0.01878  -0.1182   0.5006   1.0000
   7.250   1.3189   0.02753   0.01944  -0.1160   0.4917   1.0000
   7.500   1.3564   0.02755   0.01934  -0.1172   0.4843   1.0000
   7.750   1.3597   0.02840   0.02035  -0.1134   0.4748   1.0000
   8.000   1.4019   0.02823   0.02002  -0.1153   0.4668   1.0000
   8.250   1.3992   0.02918   0.02117  -0.1106   0.4571   1.0000
   8.500   1.4408   0.02901   0.02083  -0.1123   0.4484   1.0000
   8.750   1.4359   0.02999   0.02201  -0.1073   0.4387   1.0000
   9.000   1.4727   0.02993   0.02183  -0.1084   0.4293   1.0000
   9.250   1.4696   0.03075   0.02280  -0.1036   0.4189   1.0000
   9.500   1.4897   0.03096   0.02296  -0.1021   0.4081   1.0000
   9.750   1.5059   0.03117   0.02311  -0.1000   0.3965   1.0000
  10.000   1.5032   0.03197   0.02400  -0.0954   0.3854   1.0000
  10.250   1.5210   0.03224   0.02417  -0.0936   0.3733   1.0000
  10.500   1.5293   0.03275   0.02465  -0.0907   0.3611   1.0000
  10.750   1.5264   0.03379   0.02575  -0.0866   0.3496   1.0000
  11.000   1.5403   0.03437   0.02624  -0.0847   0.3380   1.0000
  11.250   1.5436   0.03533   0.02720  -0.0816   0.3271   1.0000
  11.500   1.5441   0.03654   0.02846  -0.0785   0.3168   1.0000
  11.750   1.5631   0.03702   0.02876  -0.0774   0.3061   1.0000
  12.000   1.5499   0.03890   0.03086  -0.0733   0.2975   1.0000
  12.250   1.5667   0.03957   0.03140  -0.0721   0.2883   1.0000
  12.500   1.5558   0.04161   0.03365  -0.0687   0.2804   1.0000
  12.750   1.5714   0.04232   0.03422  -0.0676   0.2719   1.0000
  13.000   1.5584   0.04472   0.03686  -0.0645   0.2646   1.0000
  13.250   1.5705   0.04559   0.03763  -0.0633   0.2564   1.0000
  13.500   1.5575   0.04830   0.04057  -0.0608   0.2493   1.0000
  13.750   1.5634   0.04964   0.04185  -0.0594   0.2412   1.0000
  14.000   1.5526   0.05249   0.04488  -0.0576   0.2338   1.0000
  14.250   1.5575   0.05399   0.04629  -0.0564   0.2251   1.0000
  14.500   1.5429   0.05747   0.04997  -0.0551   0.2172   1.0000
  14.750   1.5450   0.05941   0.05181  -0.0541   0.2079   1.0000
  15.000   1.5325   0.06300   0.05553  -0.0533   0.1988   1.0000
  15.250   1.5268   0.06609   0.05861  -0.0526   0.1888   1.0000
  15.500   1.5281   0.06850   0.06088  -0.0519   0.1776   1.0000
  15.750   1.5285   0.07116   0.06342  -0.0513   0.1665   1.0000
  16.000   1.5156   0.07554   0.06794  -0.0512   0.1575   1.0000
  16.250   1.5187   0.07813   0.07044  -0.0508   0.1485   1.0000
  16.500   1.5136   0.08171   0.07408  -0.0509   0.1412   1.0000
  16.750   1.5120   0.08501   0.07744  -0.0510   0.1350   1.0000
  17.000   1.5038   0.08916   0.08173  -0.0515   0.1297   1.0000
  17.250   1.5137   0.09096   0.08343  -0.0513   0.1245   1.0000
  17.500   1.4957   0.09665   0.08942  -0.0527   0.1209   1.0000
  17.750   1.4959   0.09981   0.09263  -0.0533   0.1169   1.0000
  18.000   1.5076   0.10142   0.09416  -0.0532   0.1133   1.0000
  18.250   1.4876   0.10776   0.10082  -0.0553   0.1110   1.0000
  18.500   1.4738   0.11332   0.10658  -0.0573   0.1086   1.0000
  18.750   1.4797   0.11572   0.10900  -0.0578   0.1058   1.0000
  19.000   1.4945   0.11680   0.11000  -0.0576   0.1031   1.0000
  19.250   1.4616   0.12565   0.11920  -0.0618   0.1021   1.0000
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