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GOE 226 (MVA H.36) AIRFOIL (goe226-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 226 (MVA H.36) AIRFOIL (goe226-il)
Reynolds number: 100,000
Max Cl/Cd: 52.62 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe226-il-100000.txt
Download as CSV file: xf-goe226-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 226 (MVA H.36) 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
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.0084   0.10362   0.09878  -0.0887   0.9146   0.1219
  -7.500  -0.0213   0.10430   0.09949  -0.0926   0.9054   0.1263
  -7.250  -0.0552   0.10646   0.10173  -0.0914   0.8903   0.1270
  -7.000  -0.0060   0.09849   0.09371  -0.0918   0.8907   0.1295
  -6.750   0.0331   0.09410   0.08925  -0.0958   0.8885   0.1338
  -6.500   0.0146   0.09438   0.08960  -0.0907   0.8770   0.1353
  -6.250   0.0099   0.09475   0.08995  -0.1036   0.8679   0.1426
  -6.000  -0.0155   0.09465   0.08993  -0.0989   0.8548   0.1430
  -5.750   0.0181   0.08927   0.08453  -0.0943   0.8537   0.1453
  -5.500   0.0579   0.08558   0.08077  -0.0974   0.8517   0.1522
  -5.250   0.0317   0.08614   0.08140  -0.0916   0.8383   0.1540
  -5.000   0.0624   0.08207   0.07727  -0.1019   0.8343   0.1612
  -4.750   0.0351   0.08268   0.07796  -0.0948   0.8225   0.1617
  -4.500   0.0834   0.07919   0.07434  -0.1122   0.8178   0.1759
  -4.250   0.1060   0.07568   0.07084  -0.1078   0.8161   0.1781
  -4.000   0.0794   0.07624   0.07147  -0.1009   0.8037   0.1787
  -3.750   0.1309   0.07234   0.06746  -0.1123   0.8004   0.1942
  -3.500   0.1530   0.07004   0.06516  -0.1098   0.7969   0.1985
  -3.250   0.1473   0.06964   0.06479  -0.1072   0.7855   0.2032
  -3.000   0.2012   0.06545   0.06049  -0.1166   0.7829   0.2156
  -2.750   0.4567   0.03684   0.02898  -0.1910   0.7864   0.1434
  -2.500   0.5020   0.03542   0.02759  -0.1936   0.7837   0.1522
  -2.250   0.5538   0.03349   0.02533  -0.1973   0.7819   0.1627
  -2.000   0.5643   0.03407   0.02591  -0.1952   0.7702   0.1699
  -1.750   0.6096   0.03269   0.02442  -0.1974   0.7672   0.1841
  -1.500   0.6555   0.03137   0.02303  -0.1993   0.7649   0.2031
  -1.250   0.6702   0.03179   0.02347  -0.1976   0.7532   0.2155
  -1.000   0.7122   0.03075   0.02242  -0.1988   0.7500   0.2383
  -0.750   0.7551   0.02966   0.02127  -0.2002   0.7475   0.2658
  -0.500   0.7705   0.03015   0.02185  -0.1984   0.7355   0.2856
  -0.250   0.8112   0.02911   0.02086  -0.1993   0.7322   0.3226
   0.000   0.8335   0.02922   0.02104  -0.1981   0.7220   0.3557
   0.250   0.8701   0.02840   0.02025  -0.1983   0.7168   0.3926
   0.500   0.9110   0.02734   0.01919  -0.1991   0.7136   0.4241
   0.750   0.9306   0.02759   0.01946  -0.1975   0.7013   0.4466
   1.000   0.9705   0.02660   0.01843  -0.1983   0.6972   0.4721
   1.250   0.9913   0.02680   0.01868  -0.1970   0.6853   0.4915
   1.500   1.0302   0.02595   0.01776  -0.1978   0.6804   0.5214
   1.750   1.0511   0.02616   0.01805  -0.1964   0.6685   0.5452
   2.000   1.0896   0.02538   0.01720  -0.1971   0.6629   0.5755
   2.250   1.1103   0.02569   0.01756  -0.1959   0.6509   0.5978
   2.500   1.1478   0.02509   0.01684  -0.1967   0.6453   0.6284
   2.750   1.1667   0.02558   0.01740  -0.1954   0.6337   0.6570
   3.000   1.2025   0.02497   0.01674  -0.1960   0.6280   0.7006
   3.250   1.2187   0.02532   0.01732  -0.1943   0.6172   0.7565
   3.500   1.2508   0.02476   0.01681  -0.1945   0.6112   1.0000
   3.750   1.2716   0.02559   0.01757  -0.1939   0.6016   1.0000
   4.000   1.3039   0.02565   0.01745  -0.1944   0.5950   1.0000
   4.250   1.3267   0.02625   0.01799  -0.1937   0.5869   1.0000
   4.500   1.3530   0.02651   0.01817  -0.1934   0.5792   1.0000
   4.750   1.3829   0.02665   0.01818  -0.1935   0.5727   1.0000
   5.000   1.4006   0.02737   0.01894  -0.1921   0.5640   1.0000
   5.250   1.4349   0.02727   0.01869  -0.1928   0.5588   1.0000
   5.500   1.4481   0.02833   0.01985  -0.1909   0.5508   1.0000
   5.750   1.4747   0.02861   0.02009  -0.1906   0.5447   1.0000
   6.000   1.5053   0.02879   0.02019  -0.1909   0.5396   1.0000
   6.250   1.5162   0.02990   0.02144  -0.1886   0.5318   1.0000
   6.500   1.5472   0.02996   0.02142  -0.1889   0.5265   1.0000
   6.750   1.5660   0.03077   0.02229  -0.1877   0.5204   1.0000
   7.000   1.5828   0.03160   0.02320  -0.1863   0.5139   1.0000
   7.250   1.6176   0.03154   0.02305  -0.1871   0.5091   1.0000
   7.500   1.6267   0.03281   0.02448  -0.1846   0.5022   1.0000
   7.750   1.6489   0.03331   0.02501  -0.1838   0.4959   1.0000
   8.000   1.6892   0.03309   0.02465  -0.1854   0.4909   1.0000
   8.250   1.6856   0.03488   0.02669  -0.1813   0.4833   1.0000
   8.500   1.7162   0.03508   0.02687  -0.1816   0.4777   1.0000
   8.750   1.7378   0.03588   0.02772  -0.1808   0.4719   1.0000
   9.000   1.7425   0.03734   0.02934  -0.1778   0.4650   1.0000
   9.250   1.7844   0.03718   0.02910  -0.1796   0.4595   1.0000
   9.500   1.7808   0.03909   0.03121  -0.1756   0.4525   1.0000
   9.750   1.8001   0.03983   0.03201  -0.1745   0.4456   1.0000
  10.000   1.8332   0.04010   0.03225  -0.1751   0.4388   1.0000
  10.250   1.8201   0.04224   0.03462  -0.1699   0.4314   1.0000
  10.500   1.8803   0.04112   0.03327  -0.1738   0.4230   1.0000
  10.750   1.8446   0.04410   0.03660  -0.1657   0.4167   1.0000
  11.000   1.9078   0.04264   0.03493  -0.1699   0.4070   1.0000
  11.250   1.8730   0.04552   0.03811  -0.1620   0.4013   1.0000
  11.500   1.8685   0.04711   0.03982  -0.1581   0.3944   1.0000
  11.750   1.9124   0.04649   0.03913  -0.1597   0.3867   1.0000
  12.000   1.8598   0.05088   0.04385  -0.1512   0.3817   1.0000
  12.250   1.9248   0.04820   0.04100  -0.1543   0.3724   1.0000
  12.500   1.8813   0.05235   0.04543  -0.1473   0.3675   1.0000
  12.750   1.8237   0.05853   0.05189  -0.1408   0.3623   1.0000
  13.000   1.9078   0.05312   0.04628  -0.1438   0.3531   1.0000
  13.250   1.8199   0.06232   0.05588  -0.1361   0.3493   1.0000
  13.750   1.8457   0.06295   0.05662  -0.1331   0.3352   1.0000
  14.250   1.8638   0.06422   0.05801  -0.1298   0.3211   1.0000
  15.000   1.7326   0.08649   0.08086  -0.1242   0.3050   1.0000
  15.250   1.2453   0.18685   0.18108  -0.1633   0.2878   1.0000
  15.500   1.2494   0.18917   0.18348  -0.1642   0.2792   1.0000
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