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GOE 482 AIRFOIL (goe482-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 482 AIRFOIL (goe482-il)
Reynolds number: 100,000
Max Cl/Cd: 35.76 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe482-il-100000.txt
Download as CSV file: xf-goe482-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 482 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.1812   0.10772   0.10279  -0.1236   0.9068   0.1066
 -10.000   0.2033   0.10446   0.09946  -0.1286   0.9030   0.1118
  -9.750   0.1788   0.10719   0.10224  -0.1319   0.8893   0.1146
  -9.500   0.2215   0.09930   0.09428  -0.1334   0.8868   0.1170
  -9.250   0.2377   0.09665   0.09160  -0.1329   0.8773   0.1201
  -9.000   0.2543   0.09406   0.08896  -0.1352   0.8705   0.1249
  -8.750   0.2348   0.09570   0.09063  -0.1364   0.8573   0.1290
  -8.500   0.2436   0.09246   0.08735  -0.1390   0.8510   0.1306
  -8.250   0.2705   0.08843   0.08328  -0.1367   0.8421   0.1333
  -8.000   0.2893   0.08584   0.08063  -0.1373   0.8349   0.1378
  -7.750   0.2878   0.08507   0.07987  -0.1364   0.8237   0.1421
  -7.500   0.2496   0.08805   0.08291  -0.1366   0.8103   0.1455
  -7.250   0.2582   0.08463   0.07949  -0.1359   0.8016   0.1469
  -7.000   0.3041   0.07952   0.07424  -0.1363   0.7980   0.1504
  -6.750   0.3079   0.07846   0.07320  -0.1342   0.7873   0.1539
  -6.500   0.3063   0.07760   0.07230  -0.1342   0.7797   0.1602
  -6.250   0.2574   0.08099   0.07583  -0.1376   0.7648   0.1634
  -6.000   0.2936   0.07549   0.07024  -0.1327   0.7619   0.1656
  -5.750   0.2997   0.07418   0.06896  -0.1294   0.7524   0.1678
  -5.500   0.3133   0.07234   0.06708  -0.1289   0.7461   0.1723
  -5.000   0.3046   0.07037   0.06514  -0.1327   0.7292   0.1831
  -4.750   0.3309   0.06764   0.06233  -0.1305   0.7258   0.1870
  -4.500   0.3227   0.06765   0.06242  -0.1268   0.7155   0.1908
  -4.250   0.3381   0.06524   0.05993  -0.1343   0.7101   0.2020
  -4.000   0.3647   0.06272   0.05733  -0.1328   0.7073   0.2065
  -3.750   0.3492   0.06322   0.05796  -0.1284   0.6959   0.2097
  -3.500   0.3796   0.06018   0.05479  -0.1353   0.6922   0.2220
  -3.250   0.3702   0.06038   0.05507  -0.1305   0.6831   0.2246
  -3.000   0.3994   0.05803   0.05261  -0.1364   0.6778   0.2398
  -2.750   0.5273   0.04078   0.03389  -0.1762   0.6756   0.1488
  -2.500   0.5809   0.03700   0.02952  -0.1823   0.6733   0.1404
  -2.250   0.5857   0.03716   0.02957  -0.1805   0.6631   0.1389
  -2.000   0.6291   0.03519   0.02717  -0.1835   0.6595   0.1401
  -1.750   0.6753   0.03330   0.02482  -0.1865   0.6568   0.1411
  -1.500   0.6807   0.03404   0.02549  -0.1841   0.6475   0.1415
  -1.250   0.7176   0.03297   0.02410  -0.1854   0.6434   0.1432
  -1.000   0.7601   0.03167   0.02249  -0.1873   0.6405   0.1468
  -0.750   0.7684   0.03239   0.02332  -0.1851   0.6326   0.1503
  -0.500   0.7964   0.03210   0.02297  -0.1851   0.6274   0.1565
  -0.250   0.8366   0.03114   0.02179  -0.1864   0.6243   0.1637
   0.000   0.8801   0.02995   0.02058  -0.1883   0.6218   0.1767
   0.250   0.8723   0.03179   0.02258  -0.1840   0.6118   0.1827
   0.500   0.9096   0.03093   0.02183  -0.1852   0.6082   0.2134
   0.750   0.9551   0.02975   0.02119  -0.1875   0.6056   0.3884
   1.000   0.9484   0.03174   0.02340  -0.1834   0.5964   0.4342
   1.250   0.9801   0.03148   0.02325  -0.1834   0.5923   0.5055
   1.500   1.0199   0.03085   0.02261  -0.1844   0.5894   0.5737
   1.750   1.0153   0.03277   0.02471  -0.1805   0.5815   0.6066
   2.000   1.0348   0.03309   0.02518  -0.1790   0.5763   0.6659
   2.250   1.0681   0.03225   0.02452  -0.1787   0.5733   0.7613
   2.500   1.1122   0.03110   0.02332  -0.1804   0.5709   1.0000
   2.750   1.0784   0.03480   0.02720  -0.1736   0.5599   1.0000
   3.000   1.1247   0.03420   0.02631  -0.1760   0.5569   1.0000
   3.250   1.1743   0.03350   0.02532  -0.1787   0.5545   1.0000
   3.500   0.9287   0.05366   0.04644  -0.1559   0.5222   1.0000
   3.750   0.9772   0.05171   0.04423  -0.1566   0.5217   1.0000
   4.000   1.0302   0.04943   0.04171  -0.1576   0.5215   1.0000
   4.250   1.0889   0.04693   0.03899  -0.1593   0.5214   1.0000
   4.500   1.1522   0.04450   0.03635  -0.1619   0.5211   1.0000
   4.750   1.2164   0.04249   0.03414  -0.1653   0.5203   1.0000
   5.000   1.2832   0.04087   0.03233  -0.1697   0.5192   1.0000
   8.000   0.8021   0.13821   0.13113  -0.1561   0.4757   1.0000
   8.250   0.8227   0.14010   0.13297  -0.1562   0.4708   1.0000
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