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GOE 498 AIRFOIL (goe498-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 498 AIRFOIL (goe498-il)
Reynolds number: 200,000
Max Cl/Cd: 73.49 at α=5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe498-il-200000-n5.txt
Download as CSV file: xf-goe498-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250  -0.6194   0.06361   0.05882  -0.0923   0.9926   0.0476
 -13.000  -0.6638   0.05102   0.04581  -0.1066   0.9842   0.0480
 -12.750  -0.6782   0.04392   0.03839  -0.1159   0.9754   0.0484
 -12.500  -0.6683   0.04024   0.03458  -0.1218   0.9695   0.0489
 -12.250  -0.6633   0.03761   0.03187  -0.1250   0.9603   0.0493
 -12.000  -0.6406   0.03515   0.02930  -0.1299   0.9557   0.0500
 -11.750  -0.6273   0.03340   0.02743  -0.1313   0.9477   0.0506
 -11.500  -0.6044   0.03163   0.02549  -0.1338   0.9430   0.0516
 -11.250  -0.5770   0.02984   0.02347  -0.1369   0.9401   0.0529
 -11.000  -0.5624   0.02845   0.02185  -0.1367   0.9319   0.0540
 -10.750  -0.5335   0.02748   0.02089  -0.1382   0.9278   0.0549
 -10.500  -0.5010   0.02647   0.01982  -0.1404   0.9249   0.0559
 -10.250  -0.4743   0.02553   0.01877  -0.1412   0.9200   0.0571
 -10.000  -0.4516   0.02461   0.01771  -0.1413   0.9129   0.0585
  -9.750  -0.4209   0.02363   0.01657  -0.1427   0.9085   0.0600
  -9.500  -0.3865   0.02285   0.01578  -0.1446   0.9052   0.0614
  -9.250  -0.3663   0.02228   0.01516  -0.1436   0.8963   0.0629
  -9.000  -0.3368   0.02155   0.01431  -0.1444   0.8904   0.0648
  -8.750  -0.3031   0.02077   0.01339  -0.1460   0.8862   0.0666
  -8.500  -0.2827   0.02025   0.01288  -0.1449   0.8767   0.0680
  -8.250  -0.2536   0.01967   0.01224  -0.1454   0.8702   0.0701
  -8.000  -0.2233   0.01911   0.01155  -0.1460   0.8641   0.0725
  -7.750  -0.2009   0.01859   0.01101  -0.1452   0.8545   0.0743
  -7.500  -0.1706   0.01803   0.01042  -0.1459   0.8481   0.0766
  -7.250  -0.1466   0.01761   0.00994  -0.1452   0.8388   0.0789
  -7.000  -0.1181   0.01715   0.00938  -0.1454   0.8308   0.0816
  -6.750  -0.0921   0.01666   0.00890  -0.1452   0.8222   0.0841
  -6.500  -0.0650   0.01627   0.00844  -0.1451   0.8135   0.0872
  -6.250  -0.0369   0.01588   0.00799  -0.1451   0.8054   0.0903
  -6.000  -0.0104   0.01549   0.00758  -0.1449   0.7960   0.0938
  -5.750   0.0183   0.01516   0.00718  -0.1450   0.7880   0.0980
  -5.500   0.0450   0.01485   0.00687  -0.1447   0.7791   0.1025
  -5.000   0.1009   0.01433   0.00630  -0.1446   0.7627   0.1159
  -4.750   0.1296   0.01411   0.00605  -0.1446   0.7548   0.1258
  -4.500   0.1569   0.01393   0.00586  -0.1444   0.7469   0.1381
  -4.250   0.1846   0.01377   0.00567  -0.1442   0.7393   0.1512
  -4.000   0.2133   0.01363   0.00547  -0.1442   0.7323   0.1640
  -3.500   0.2676   0.01340   0.00521  -0.1437   0.7170   0.1886
  -3.250   0.2952   0.01332   0.00512  -0.1435   0.7103   0.2008
  -3.000   0.3218   0.01326   0.00506  -0.1431   0.7026   0.2133
  -2.750   0.3499   0.01322   0.00498  -0.1429   0.6955   0.2270
  -2.500   0.3765   0.01318   0.00496  -0.1425   0.6882   0.2410
  -2.250   0.4029   0.01316   0.00494  -0.1420   0.6792   0.2558
  -2.000   0.4299   0.01316   0.00489  -0.1416   0.6704   0.2692
  -1.750   0.4555   0.01316   0.00487  -0.1410   0.6607   0.2828
  -1.500   0.4827   0.01316   0.00485  -0.1406   0.6530   0.2971
  -1.250   0.5084   0.01316   0.00488  -0.1400   0.6450   0.3100
  -1.000   0.5349   0.01318   0.00487  -0.1395   0.6374   0.3225
  -0.750   0.5615   0.01319   0.00489  -0.1391   0.6306   0.3352
  -0.500   0.5874   0.01322   0.00492  -0.1385   0.6230   0.3483
  -0.250   0.6136   0.01324   0.00495  -0.1380   0.6157   0.3613
   0.000   0.6393   0.01327   0.00499  -0.1374   0.6075   0.3733
   0.250   0.6645   0.01331   0.00501  -0.1367   0.5985   0.3857
   0.500   0.6897   0.01334   0.00505  -0.1360   0.5896   0.3974
   0.750   0.7146   0.01340   0.00510  -0.1352   0.5802   0.4102
   1.000   0.7397   0.01345   0.00516  -0.1345   0.5720   0.4229
   1.250   0.7645   0.01352   0.00525  -0.1337   0.5634   0.4368
   1.500   0.7894   0.01361   0.00532  -0.1330   0.5557   0.4538
   1.750   0.8137   0.01367   0.00546  -0.1322   0.5473   0.4743
   2.000   0.8380   0.01377   0.00559  -0.1313   0.5393   0.4974
   2.500   0.8853   0.01397   0.00587  -0.1294   0.5222   0.5433
   2.750   0.9087   0.01409   0.00602  -0.1284   0.5138   0.5655
   3.000   0.9319   0.01421   0.00618  -0.1274   0.5053   0.5860
   3.250   0.9552   0.01435   0.00632  -0.1264   0.4979   0.6059
   3.500   0.9777   0.01444   0.00651  -0.1253   0.4897   0.6278
   3.750   0.9990   0.01457   0.00667  -0.1239   0.4816   0.6534
   4.000   1.0202   0.01465   0.00686  -0.1225   0.4730   0.6853
   4.250   1.0406   0.01472   0.00705  -0.1209   0.4640   0.7359
   4.500   1.0685   0.01458   0.00722  -0.1207   0.4546   1.0000
   4.750   1.0890   0.01484   0.00742  -0.1194   0.4455   1.0000
   5.000   1.1089   0.01509   0.00764  -0.1178   0.4367   1.0000
   5.250   1.1276   0.01537   0.00787  -0.1161   0.4278   1.0000
   5.500   1.1470   0.01566   0.00812  -0.1146   0.4200   1.0000
   5.750   1.1655   0.01596   0.00840  -0.1129   0.4114   1.0000
   6.000   1.1835   0.01630   0.00869  -0.1111   0.4032   1.0000
   6.250   1.2015   0.01664   0.00901  -0.1094   0.3946   1.0000
   6.500   1.2185   0.01702   0.00935  -0.1076   0.3866   1.0000
   6.750   1.2359   0.01740   0.00972  -0.1058   0.3778   1.0000
   7.000   1.2516   0.01785   0.01011  -0.1039   0.3701   1.0000
   7.250   1.2696   0.01824   0.01053  -0.1023   0.3627   1.0000
   7.500   1.2854   0.01871   0.01098  -0.1005   0.3554   1.0000
   7.750   1.3020   0.01917   0.01144  -0.0988   0.3487   1.0000
   8.000   1.3178   0.01967   0.01195  -0.0970   0.3412   1.0000
   8.250   1.3313   0.02026   0.01251  -0.0950   0.3338   1.0000
   8.500   1.3461   0.02082   0.01309  -0.0932   0.3248   1.0000
   8.750   1.3570   0.02154   0.01377  -0.0909   0.3160   1.0000
   9.000   1.3707   0.02218   0.01444  -0.0891   0.3062   1.0000
   9.250   1.3805   0.02301   0.01524  -0.0869   0.2966   1.0000
   9.500   1.3920   0.02380   0.01605  -0.0849   0.2858   1.0000
   9.750   1.4013   0.02472   0.01696  -0.0828   0.2743   1.0000
  10.000   1.4086   0.02579   0.01800  -0.0806   0.2619   1.0000
  10.250   1.4148   0.02697   0.01915  -0.0785   0.2480   1.0000
  10.500   1.4203   0.02826   0.02041  -0.0764   0.2333   1.0000
  10.750   1.4243   0.02971   0.02182  -0.0743   0.2191   1.0000
  11.000   1.4281   0.03126   0.02333  -0.0723   0.2070   1.0000
  11.250   1.4313   0.03293   0.02498  -0.0705   0.1974   1.0000
  11.500   1.4334   0.03475   0.02678  -0.0688   0.1897   1.0000
  11.750   1.4384   0.03645   0.02849  -0.0674   0.1835   1.0000
  12.000   1.4417   0.03833   0.03037  -0.0660   0.1781   1.0000
  12.250   1.4452   0.04027   0.03233  -0.0647   0.1736   1.0000
  12.500   1.4518   0.04201   0.03413  -0.0637   0.1694   1.0000
  12.750   1.4560   0.04399   0.03615  -0.0627   0.1651   1.0000
  13.000   1.4579   0.04624   0.03841  -0.0617   0.1611   1.0000
  13.250   1.4642   0.04814   0.04038  -0.0609   0.1574   1.0000
  13.500   1.4705   0.05008   0.04240  -0.0603   0.1533   1.0000
  13.750   1.4735   0.05238   0.04475  -0.0596   0.1492   1.0000
  14.000   1.4742   0.05498   0.04736  -0.0590   0.1454   1.0000
  14.250   1.4825   0.05686   0.04938  -0.0587   0.1409   1.0000
  14.500   1.4856   0.05935   0.05194  -0.0584   0.1356   1.0000
  14.750   1.4874   0.06201   0.05467  -0.0581   0.1305   1.0000
  15.000   1.4920   0.06445   0.05721  -0.0580   0.1236   1.0000
  15.250   1.4935   0.06730   0.06013  -0.0580   0.1157   1.0000
  15.500   1.4920   0.07059   0.06345  -0.0582   0.1048   1.0000
  15.750   1.4856   0.07457   0.06740  -0.0585   0.0944   1.0000
  16.000   1.4775   0.07887   0.07168  -0.0591   0.0874   1.0000
  16.250   1.4691   0.08332   0.07614  -0.0598   0.0825   1.0000
  16.500   1.4630   0.08752   0.08040  -0.0606   0.0787   1.0000
  16.750   1.4557   0.09196   0.08488  -0.0615   0.0756   1.0000
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