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GOE 462 AIRFOIL (goe462-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: GOE 462 AIRFOIL (goe462-il)
Reynolds number: 200,000
Max Cl/Cd: 62.43 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe462-il-200000-n5.txt
Download as CSV file: xf-goe462-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 462 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500   0.1979   0.10392   0.09962  -0.0851   0.7004   0.0200
  -9.250   0.2068   0.10192   0.09753  -0.0857   0.6805   0.0208
  -9.000   0.2154   0.10011   0.09563  -0.0864   0.6623   0.0212
  -8.750   0.2240   0.09842   0.09384  -0.0870   0.6455   0.0214
  -8.500   0.2324   0.09675   0.09211  -0.0876   0.6308   0.0215
  -8.250   0.2384   0.09590   0.09121  -0.0887   0.6178   0.0217
  -8.000   0.2459   0.09429   0.08954  -0.0892   0.6053   0.0217
  -7.750   0.2581   0.09013   0.08531  -0.0887   0.5932   0.0221
  -7.500   0.2685   0.08788   0.08302  -0.0887   0.5831   0.0224
  -7.250   0.2781   0.08604   0.08113  -0.0887   0.5736   0.0228
  -7.000   0.2874   0.08426   0.07932  -0.0888   0.5645   0.0232
  -6.750   0.2958   0.08260   0.07761  -0.0888   0.5565   0.0235
  -6.500   0.3043   0.08103   0.07602  -0.0888   0.5476   0.0241
  -6.250   0.3152   0.07928   0.07423  -0.0895   0.5409   0.0247
  -6.000   0.3271   0.07746   0.07240  -0.0904   0.5331   0.0254
  -5.750   0.3396   0.07562   0.07051  -0.0915   0.5260   0.0264
  -5.500   0.3557   0.07388   0.06876  -0.0943   0.5193   0.0284
  -5.250   0.3740   0.07226   0.06711  -0.0978   0.5128   0.0288
  -5.000   0.3935   0.07033   0.06513  -0.1011   0.5069   0.0290
  -4.250   0.4381   0.06301   0.05772  -0.1029   0.4872   0.0255
  -4.000   0.4606   0.06023   0.05490  -0.1064   0.4806   0.0236
  -3.750   0.4860   0.05739   0.05199  -0.1106   0.4742   0.0229
  -3.500   0.5089   0.05596   0.05053  -0.1126   0.4668   0.0255
  -3.250   0.5374   0.05353   0.04799  -0.1168   0.4600   0.0266
  -3.000   0.5703   0.05072   0.04513  -0.1219   0.4534   0.0269
  -2.750   0.6194   0.04651   0.04077  -0.1320   0.4466   0.0292
  -2.500   0.6385   0.04605   0.04027  -0.1315   0.4394   0.0314
  -2.250   0.6740   0.04395   0.03805  -0.1360   0.4317   0.0329
  -2.000   0.7190   0.04124   0.03517  -0.1431   0.4242   0.0367
  -1.750   0.7774   0.03731   0.03102  -0.1536   0.4160   0.0395
  -1.500   0.7998   0.03723   0.03087  -0.1534   0.4091   0.0419
  -1.250   0.8393   0.03563   0.02913  -0.1577   0.4018   0.0446
  -1.000   0.8902   0.03309   0.02633  -0.1651   0.3952   0.0475
  -0.750   0.9445   0.03037   0.02338  -0.1730   0.3886   0.0510
  -0.500   0.9757   0.02981   0.02269  -0.1745   0.3822   0.0528
   0.000   1.0542   0.02749   0.02000  -0.1815   0.3703   0.0630
   0.250   1.0829   0.02730   0.01970  -0.1821   0.3650   0.0688
   0.500   1.1155   0.02683   0.01907  -0.1837   0.3605   0.0763
   0.750   1.1506   0.02626   0.01835  -0.1858   0.3559   0.0861
   1.000   1.1732   0.02654   0.01859  -0.1850   0.3517   0.0900
   1.250   1.2004   0.02662   0.01855  -0.1853   0.3478   0.0988
   1.500   1.2259   0.02666   0.01852  -0.1852   0.3441   0.1037
   1.750   1.2583   0.02635   0.01809  -0.1865   0.3400   0.1093
   2.000   1.2840   0.02627   0.01795  -0.1865   0.3361   0.1113
   2.250   1.3119   0.02611   0.01767  -0.1870   0.3326   0.1130
   2.500   1.3403   0.02600   0.01741  -0.1876   0.3296   0.1149
   2.750   1.3717   0.02578   0.01709  -0.1886   0.3266   0.1179
   3.000   1.3983   0.02574   0.01704  -0.1888   0.3236   0.1207
   3.250   1.4234   0.02577   0.01703  -0.1887   0.3206   0.1225
   3.500   1.4498   0.02576   0.01694  -0.1888   0.3179   0.1238
   3.750   1.4760   0.02581   0.01689  -0.1889   0.3152   0.1255
   4.000   1.5026   0.02587   0.01686  -0.1890   0.3126   0.1274
   4.500   1.5545   0.02598   0.01696  -0.1890   0.3070   0.1324
   4.750   1.5775   0.02617   0.01716  -0.1885   0.3044   0.1348
   5.000   1.6015   0.02635   0.01730  -0.1882   0.3021   0.1370
   5.250   1.6257   0.02655   0.01744  -0.1879   0.2999   0.1386
   5.500   1.6499   0.02682   0.01761  -0.1875   0.2979   0.1404
   5.750   1.6750   0.02703   0.01779  -0.1873   0.2959   0.1428
   6.000   1.6966   0.02725   0.01810  -0.1867   0.2938   0.1441
   6.250   1.7176   0.02754   0.01849  -0.1859   0.2915   0.1464
   6.500   1.7380   0.02784   0.01883  -0.1851   0.2887   0.1493
   6.750   1.7546   0.02816   0.01907  -0.1836   0.2832   0.1507
   7.000   1.7697   0.02843   0.01938  -0.1819   0.2764   0.1517
   7.250   1.7828   0.02878   0.01976  -0.1798   0.2708   0.1528
   7.500   1.7936   0.02937   0.02025  -0.1776   0.2656   0.1540
   7.750   1.8092   0.02977   0.02075  -0.1761   0.2592   0.1553
   8.000   1.8175   0.03051   0.02148  -0.1739   0.2518   0.1561
   8.250   1.8283   0.03124   0.02229  -0.1722   0.2436   0.1576
   8.500   1.8331   0.03240   0.02345  -0.1700   0.2347   0.1593
   8.750   1.8348   0.03395   0.02494  -0.1677   0.2168   0.1609
   9.000   1.8324   0.03603   0.02692  -0.1655   0.1980   0.1621
   9.250   1.8219   0.03904   0.02980  -0.1631   0.1763   0.1625
   9.500   1.7990   0.04360   0.03420  -0.1606   0.1471   0.1625
   9.750   1.7722   0.04911   0.03963  -0.1589   0.1211   0.1625
  10.000   1.7460   0.05510   0.04563  -0.1580   0.0993   0.1625
  10.250   1.7204   0.06155   0.05213  -0.1578   0.0815   0.1625
  10.500   1.6951   0.06844   0.05912  -0.1582   0.0651   0.1624
  10.750   1.6706   0.07565   0.06645  -0.1591   0.0486   0.1625
  11.000   1.6480   0.08293   0.07386  -0.1604   0.0286   0.1625
  11.250   1.6327   0.08929   0.08034  -0.1616   0.0237   0.1627
  11.500   1.6225   0.09493   0.08614  -0.1627   0.0205   0.1630
  11.750   1.6129   0.10062   0.09199  -0.1640   0.0193   0.1633
  12.000   1.6027   0.10649   0.09804  -0.1655   0.0185   0.1637
  12.250   1.5925   0.11248   0.10419  -0.1671   0.0179   0.1641
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