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GOE 499 AIRFOIL (goe499-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: GOE 499 AIRFOIL (goe499-il)
Reynolds number: 500,000
Max Cl/Cd: 118.27 at α=1.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe499-il-500000-n5.txt
Download as CSV file: xf-goe499-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.2228   0.09602   0.09365  -0.0693   0.9752   0.0078
  -9.250  -0.2128   0.09201   0.08964  -0.0724   0.9706   0.0082
  -9.000  -0.2026   0.08644   0.08408  -0.0773   0.9672   0.0093
  -8.750  -0.1899   0.08159   0.07922  -0.0824   0.9635   0.0099
  -8.500  -0.1738   0.07799   0.07561  -0.0868   0.9585   0.0101
  -8.250  -0.1530   0.07512   0.07272  -0.0913   0.9548   0.0108
  -8.000  -0.1369   0.07119   0.06878  -0.0962   0.9484   0.0113
  -7.750  -0.1234   0.06625   0.06381  -0.1023   0.9399   0.0126
  -7.500  -0.1184   0.05655   0.05409  -0.1145   0.9259   0.0147
  -7.250  -0.0973   0.05563   0.05314  -0.1163   0.9197   0.0152
  -7.000  -0.0766   0.05334   0.05080  -0.1201   0.9132   0.0158
  -6.750  -0.0569   0.04994   0.04736  -0.1253   0.9061   0.0168
  -6.500  -0.0320   0.04294   0.04026  -0.1366   0.8980   0.0191
  -6.250   0.0254   0.01922   0.01516  -0.1712   0.8884   0.0232
  -6.000   0.0534   0.01805   0.01387  -0.1726   0.8850   0.0245
  -5.750   0.0815   0.01736   0.01303  -0.1734   0.8815   0.0256
  -5.500   0.1094   0.01643   0.01190  -0.1742   0.8766   0.0266
  -5.250   0.1375   0.01569   0.01098  -0.1748   0.8718   0.0279
  -5.000   0.1661   0.01474   0.00979  -0.1755   0.8675   0.0287
  -4.750   0.1943   0.01388   0.00873  -0.1760   0.8628   0.0292
  -4.500   0.2227   0.01309   0.00773  -0.1764   0.8585   0.0295
  -4.250   0.2512   0.01241   0.00686  -0.1768   0.8545   0.0297
  -4.000   0.2791   0.01184   0.00617  -0.1770   0.8497   0.0300
  -3.750   0.3072   0.01136   0.00556  -0.1772   0.8454   0.0304
  -3.250   0.3636   0.01036   0.00432  -0.1775   0.8370   0.0301
  -3.000   0.3917   0.00995   0.00382  -0.1776   0.8324   0.0299
  -2.750   0.4199   0.00960   0.00337  -0.1777   0.8284   0.0298
  -2.500   0.4479   0.00930   0.00301  -0.1778   0.8236   0.0298
  -2.250   0.4759   0.00903   0.00270  -0.1779   0.8188   0.0298
  -2.000   0.5041   0.00882   0.00240  -0.1779   0.8143   0.0298
  -1.750   0.5319   0.00862   0.00217  -0.1779   0.8086   0.0300
  -1.500   0.5598   0.00847   0.00197  -0.1779   0.8032   0.0303
  -1.250   0.5878   0.00835   0.00179  -0.1779   0.7987   0.0308
  -1.000   0.6156   0.00825   0.00167  -0.1779   0.7936   0.0316
  -0.750   0.6434   0.00818   0.00157  -0.1778   0.7885   0.0328
  -0.500   0.6712   0.00812   0.00148  -0.1777   0.7839   0.0350
  -0.250   0.6988   0.00805   0.00142  -0.1777   0.7780   0.0406
   0.000   0.7263   0.00790   0.00138  -0.1776   0.7703   0.0836
   0.250   0.7535   0.00781   0.00139  -0.1775   0.7609   0.1192
   0.500   0.7807   0.00774   0.00143  -0.1774   0.7516   0.1588
   0.750   0.8075   0.00770   0.00147  -0.1772   0.7403   0.1992
   1.250   0.8597   0.00766   0.00161  -0.1765   0.7035   0.2970
   1.500   0.8851   0.00762   0.00172  -0.1760   0.6789   0.3839
   1.750   0.9095   0.00769   0.00187  -0.1753   0.6492   0.4716
   2.000   0.9293   0.00811   0.00209  -0.1737   0.5862   0.5266
   2.250   0.9464   0.00880   0.00247  -0.1717   0.5093   0.5781
   2.500   0.9687   0.00906   0.00275  -0.1707   0.4753   0.6521
   3.000   1.0112   0.00931   0.00322  -0.1681   0.4107   1.0000
   3.250   1.0320   0.00990   0.00352  -0.1669   0.3519   1.0000
   3.500   1.0375   0.01207   0.00454  -0.1634   0.1290   1.0000
   3.750   1.0537   0.01330   0.00527  -0.1615   0.0252   1.0000
   4.000   1.0776   0.01366   0.00565  -0.1608   0.0179   1.0000
   4.250   1.1013   0.01404   0.00605  -0.1600   0.0151   1.0000
   4.500   1.1238   0.01454   0.00663  -0.1590   0.0118   1.0000
   4.750   1.1460   0.01506   0.00722  -0.1579   0.0108   1.0000
   5.000   1.1682   0.01555   0.00776  -0.1568   0.0101   1.0000
   5.250   1.1895   0.01612   0.00840  -0.1556   0.0093   1.0000
   5.500   1.2107   0.01664   0.00895  -0.1545   0.0083   1.0000
   5.750   1.2310   0.01723   0.00956  -0.1532   0.0076   1.0000
   6.000   1.2463   0.01829   0.01069  -0.1510   0.0071   1.0000
   6.250   1.2628   0.01917   0.01164  -0.1490   0.0068   1.0000
   6.500   1.2793   0.02002   0.01259  -0.1471   0.0065   1.0000
   6.750   1.2936   0.02099   0.01364  -0.1447   0.0062   1.0000
   7.000   1.3064   0.02206   0.01479  -0.1421   0.0060   1.0000
   7.250   1.3195   0.02319   0.01600  -0.1396   0.0057   1.0000
   7.500   1.3344   0.02415   0.01703  -0.1375   0.0054   1.0000
   7.750   1.3499   0.02500   0.01793  -0.1356   0.0050   1.0000
   8.000   1.3651   0.02575   0.01871  -0.1338   0.0048   1.0000
   8.250   1.3784   0.02713   0.02014  -0.1318   0.0045   1.0000
   8.500   1.3943   0.02901   0.02215  -0.1300   0.0044   1.0000
   8.750   1.4129   0.03068   0.02403  -0.1286   0.0042   1.0000
   9.000   1.4356   0.03300   0.02658  -0.1278   0.0040   1.0000
   9.250   1.4613   0.03617   0.03006  -0.1275   0.0038   1.0000
   9.500   1.4815   0.03972   0.03395  -0.1264   0.0036   1.0000
   9.750   1.4931   0.04332   0.03788  -0.1240   0.0036   1.0000
  10.000   1.4964   0.04682   0.04170  -0.1206   0.0035   1.0000
  10.250   1.4936   0.05035   0.04554  -0.1166   0.0035   1.0000
  10.500   1.4868   0.05387   0.04933  -0.1124   0.0035   1.0000
  10.750   1.4763   0.05753   0.05326  -0.1083   0.0036   1.0000
  11.000   1.4629   0.06143   0.05742  -0.1045   0.0036   1.0000
  11.250   1.4476   0.06562   0.06186  -0.1012   0.0036   1.0000
  11.500   1.4312   0.07001   0.06647  -0.0986   0.0036   1.0000
  11.750   1.4129   0.07477   0.07145  -0.0966   0.0036   1.0000
  12.000   1.3938   0.07990   0.07679  -0.0955   0.0036   1.0000
  12.250   1.3741   0.08544   0.08252  -0.0953   0.0036   1.0000
  12.500   1.3534   0.09153   0.08880  -0.0960   0.0036   1.0000
  12.750   1.3309   0.09836   0.09582  -0.0978   0.0037   1.0000
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