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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 50,000
Max Cl/Cd: 44.92 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe499-il-50000-n5.txt
Download as CSV file: xf-goe499-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 499 AIRFOIL                                 
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.3593   0.11573   0.10945  -0.0266   1.0000   0.0997
  -7.500  -0.3757   0.11581   0.10965  -0.0247   1.0000   0.1002
  -7.250  -0.3892   0.11543   0.10938  -0.0239   1.0000   0.1006
  -7.000  -0.3967   0.11436   0.10840  -0.0249   1.0000   0.1009
  -6.750  -0.3831   0.10782   0.10185  -0.0202   1.0000   0.1030
  -6.500  -0.3815   0.10505   0.09909  -0.0184   1.0000   0.1057
  -6.250  -0.3838   0.10307   0.09717  -0.0176   1.0000   0.1101
  -6.000  -0.3895   0.10209   0.09627  -0.0205   1.0000   0.1143
  -5.750  -0.3873   0.10012   0.09438  -0.0262   1.0000   0.1155
  -5.500  -0.3809   0.09556   0.08980  -0.0194   0.9991   0.1197
  -5.250  -0.3621   0.09184   0.08601  -0.0237   0.9949   0.1238
  -5.000  -0.3290   0.08798   0.08205  -0.0383   0.9888   0.1293
  -4.750  -0.2983   0.08320   0.07718  -0.0475   0.9847   0.1299
  -4.250  -0.2380   0.06983   0.06349  -0.0604   0.9779   0.0846
  -4.000  -0.2059   0.06505   0.05857  -0.0667   0.9745   0.0802
  -3.750  -0.1275   0.05431   0.04724  -0.0895   0.9728   0.0737
  -3.500  -0.1076   0.05360   0.04653  -0.0891   0.9688   0.0790
  -3.250  -0.0506   0.04815   0.04058  -0.1006   0.9670   0.0804
  -3.000   0.0148   0.04186   0.03353  -0.1135   0.9663   0.0776
  -2.750   0.0721   0.03734   0.02815  -0.1225   0.9654   0.0764
  -2.500   0.1148   0.03472   0.02486  -0.1270   0.9627   0.0764
  -2.250   0.1529   0.03303   0.02265  -0.1300   0.9591   0.0772
  -2.000   0.1915   0.03177   0.02096  -0.1327   0.9555   0.0789
  -1.750   0.2306   0.03082   0.01962  -0.1353   0.9512   0.0817
  -1.500   0.2662   0.03007   0.01847  -0.1369   0.9443   0.0856
  -1.250   0.3096   0.02956   0.01779  -0.1401   0.9387   0.0941
  -1.000   0.3429   0.02923   0.01734  -0.1414   0.9299   0.1107
  -0.750   0.3864   0.02872   0.01681  -0.1445   0.9243   0.1448
  -0.500   0.4182   0.02844   0.01668  -0.1455   0.9159   0.2085
  -0.250   0.4565   0.02838   0.01677  -0.1478   0.9102   0.2956
   0.000   0.4845   0.02830   0.01689  -0.1482   0.9017   0.3613
   0.250   0.5228   0.02807   0.01697  -0.1502   0.8966   0.4424
   0.500   0.5482   0.02794   0.01710  -0.1498   0.8876   0.5307
   0.750   0.5732   0.02702   0.01691  -0.1487   0.8804   0.8653
   1.000   0.6040   0.02723   0.01685  -0.1494   0.8717   1.0000
   1.250   0.6329   0.02752   0.01696  -0.1497   0.8624   1.0000
   1.500   0.6708   0.02765   0.01695  -0.1514   0.8560   1.0000
   1.750   0.6965   0.02796   0.01718  -0.1511   0.8453   1.0000
   2.000   0.7255   0.02820   0.01736  -0.1513   0.8356   1.0000
   2.250   0.7625   0.02822   0.01739  -0.1526   0.8285   1.0000
   2.500   0.7878   0.02851   0.01769  -0.1522   0.8170   1.0000
   2.750   0.8149   0.02874   0.01796  -0.1519   0.8059   1.0000
   3.000   0.8474   0.02879   0.01811  -0.1525   0.7969   1.0000
   3.250   0.8786   0.02884   0.01826  -0.1527   0.7870   1.0000
   3.500   0.9039   0.02909   0.01862  -0.1521   0.7746   1.0000
   3.750   0.9303   0.02930   0.01897  -0.1516   0.7625   1.0000
   4.000   0.9584   0.02945   0.01933  -0.1513   0.7511   1.0000
   4.250   0.9944   0.02928   0.01939  -0.1521   0.7428   1.0000
   4.500   1.0190   0.02957   0.01989  -0.1513   0.7297   1.0000
   4.750   1.0438   0.02987   0.02047  -0.1505   0.7168   1.0000
   5.000   1.0692   0.03017   0.02105  -0.1498   0.7042   1.0000
   5.250   1.0993   0.02892   0.02007  -0.1476   0.6776   1.0000
   5.500   1.1292   0.02651   0.01767  -0.1433   0.6127   1.0000
   5.750   1.1559   0.02573   0.01634  -0.1393   0.5038   1.0000
   6.000   1.1534   0.02745   0.01703  -0.1335   0.3373   1.0000
   6.250   1.1336   0.03185   0.01930  -0.1278   0.0922   1.0000
   6.500   1.1421   0.03408   0.02128  -0.1253   0.0593   1.0000
   6.750   1.1522   0.03594   0.02322  -0.1229   0.0518   1.0000
   7.000   1.1609   0.03785   0.02528  -0.1204   0.0470   1.0000
   7.250   1.1691   0.03974   0.02735  -0.1180   0.0427   1.0000
   7.500   1.1743   0.04193   0.02968  -0.1155   0.0397   1.0000
   7.750   1.1802   0.04415   0.03207  -0.1130   0.0383   1.0000
   8.000   1.1903   0.04614   0.03438  -0.1107   0.0372   1.0000
   8.250   1.2069   0.04801   0.03648  -0.1088   0.0359   1.0000
   8.500   1.2339   0.04976   0.03842  -0.1075   0.0336   1.0000
   8.750   1.2835   0.05239   0.04101  -0.1090   0.0303   1.0000
   9.000   1.3423   0.05627   0.04522  -0.1119   0.0295   1.0000
   9.250   1.3719   0.05999   0.04937  -0.1117   0.0293   1.0000
   9.500   1.3905   0.06378   0.05360  -0.1104   0.0293   1.0000
   9.750   1.4001   0.06747   0.05784  -0.1082   0.0292   1.0000
  10.000   1.4025   0.07105   0.06186  -0.1055   0.0290   1.0000
  10.250   1.3983   0.07451   0.06572  -0.1022   0.0288   1.0000
  10.500   1.3900   0.07797   0.06955  -0.0989   0.0286   1.0000
  10.750   1.3788   0.08161   0.07353  -0.0958   0.0285   1.0000
  11.000   1.3649   0.08546   0.07770  -0.0932   0.0284   1.0000
  11.250   1.3499   0.08964   0.08218  -0.0913   0.0285   1.0000
  11.500   1.3334   0.09411   0.08693  -0.0900   0.0285   1.0000
  11.750   1.3166   0.09892   0.09199  -0.0895   0.0286   1.0000
  12.000   1.2984   0.10412   0.09743  -0.0898   0.0287   1.0000
  12.250   1.2801   0.10973   0.10325  -0.0910   0.0288   1.0000
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