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GOE 227 (MVA H.37) AIRFOIL (goe227-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: GOE 227 (MVA H.37) AIRFOIL (goe227-il)
Reynolds number: 50,000
Max Cl/Cd: 23.35 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-goe227-il-50000-n5.txt
Download as CSV file: xf-goe227-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 227 (MVA H.37) 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
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.0961   0.13063   0.12360  -0.0789   0.9426   0.1295
 -10.000  -0.0927   0.12904   0.12201  -0.0840   0.9365   0.1311
  -9.750  -0.0919   0.12736   0.12034  -0.0872   0.9275   0.1316
  -9.500  -0.0570   0.12046   0.11338  -0.0882   0.9246   0.1341
  -9.250  -0.0325   0.11657   0.10942  -0.0909   0.9210   0.1395
  -9.000  -0.0294   0.11487   0.10773  -0.0925   0.9111   0.1446
  -8.750  -0.0309   0.11368   0.10654  -0.0968   0.9032   0.1469
  -8.500  -0.0310   0.11188   0.10475  -0.0985   0.8931   0.1472
  -8.250  -0.0249   0.10925   0.10211  -0.1006   0.8856   0.1474
  -7.750  -0.0049   0.10311   0.09592  -0.1035   0.8724   0.1472
  -7.250  -0.0099   0.09277   0.08546  -0.1079   0.8556   0.1022
  -7.000  -0.0083   0.09110   0.08381  -0.1063   0.8470   0.1016
  -6.750   0.0017   0.08854   0.08122  -0.1069   0.8411   0.1007
  -6.500   0.0161   0.08524   0.07786  -0.1096   0.8371   0.0996
  -6.250   0.0062   0.08417   0.07685  -0.1076   0.8267   0.0989
  -6.000   0.0155   0.08095   0.07359  -0.1108   0.8216   0.0988
  -5.750   0.0146   0.07860   0.07123  -0.1125   0.8147   0.0994
  -5.500   0.0138   0.07593   0.06856  -0.1150   0.8075   0.1000
  -5.250   0.0346   0.07028   0.06279  -0.1246   0.8035   0.1008
  -4.750   0.0917   0.05614   0.04800  -0.1515   0.7920   0.1033
  -4.500   0.1141   0.05547   0.04735  -0.1517   0.7885   0.1062
  -4.250   0.1760   0.04986   0.04111  -0.1662   0.7868   0.1110
  -4.000   0.2406   0.04541   0.03584  -0.1791   0.7855   0.1182
  -3.750   0.2800   0.04403   0.03427  -0.1826   0.7839   0.1227
  -3.500   0.2845   0.04440   0.03449  -0.1814   0.7758   0.1256
  -3.250   0.3256   0.04308   0.03265  -0.1858   0.7728   0.1327
  -3.000   0.3598   0.04236   0.03186  -0.1878   0.7703   0.1378
  -2.750   0.4004   0.04149   0.03061  -0.1909   0.7684   0.1462
  -2.500   0.4150   0.04190   0.03102  -0.1901   0.7628   0.1509
  -2.250   0.4356   0.04210   0.03116  -0.1901   0.7575   0.1563
  -2.000   0.4724   0.04153   0.03041  -0.1920   0.7540   0.1660
  -1.750   0.5161   0.04065   0.02943  -0.1945   0.7514   0.1782
  -1.500   0.5269   0.04133   0.03015  -0.1929   0.7417   0.1847
  -1.250   0.5655   0.04077   0.02960  -0.1946   0.7375   0.2020
  -1.000   0.6098   0.03999   0.02887  -0.1970   0.7347   0.2289
  -0.750   0.6150   0.04131   0.03033  -0.1947   0.7249   0.2466
  -0.500   0.6501   0.04118   0.03027  -0.1957   0.7211   0.2983
  -0.250   0.6891   0.04085   0.02993  -0.1968   0.7184   0.3545
   0.000   0.6905   0.04256   0.03171  -0.1940   0.7080   0.3779
   0.250   0.7232   0.04247   0.03160  -0.1941   0.7043   0.4193
   0.750   0.7598   0.04398   0.03316  -0.1915   0.6905   0.4752
   1.000   0.7931   0.04360   0.03280  -0.1913   0.6872   0.5042
   1.500   0.8314   0.04493   0.03411  -0.1891   0.6727   0.5488
   1.750   0.8687   0.04419   0.03331  -0.1895   0.6699   0.5696
   2.000   0.8741   0.04594   0.03507  -0.1876   0.6582   0.5812
   2.250   0.9097   0.04533   0.03439  -0.1880   0.6547   0.5964
   2.500   0.9495   0.04445   0.03344  -0.1889   0.6522   0.6125
   2.750   0.9503   0.04639   0.03547  -0.1864   0.6391   0.6231
   3.000   0.9885   0.04550   0.03456  -0.1869   0.6362   0.6439
   3.500   1.0246   0.04669   0.03591  -0.1846   0.6198   0.6859
   3.750   1.0613   0.04570   0.03500  -0.1847   0.6169   0.7254
   4.250   1.0884   0.04662   0.03618  -0.1807   0.5999   1.0000
   4.750   1.1184   0.04912   0.03854  -0.1788   0.5809   1.0000
   5.000   1.1162   0.05179   0.04122  -0.1766   0.5671   1.0000
   5.500   1.1445   0.05440   0.04375  -0.1745   0.5496   1.0000
   6.000   1.1371   0.06076   0.05015  -0.1709   0.5240   1.0000
   6.250   1.1610   0.06106   0.05043  -0.1703   0.5192   1.0000
   6.500   1.1928   0.06045   0.04978  -0.1699   0.5166   1.0000
   6.750   1.1827   0.06454   0.05393  -0.1682   0.5035   1.0000
   7.250   1.2014   0.06853   0.05797  -0.1661   0.4885   1.0000
   7.500   1.2309   0.06801   0.05745  -0.1654   0.4862   1.0000
   7.750   1.2173   0.07295   0.06245  -0.1641   0.4739   1.0000
   8.000   1.2450   0.07261   0.06213  -0.1634   0.4714   1.0000
   8.500   1.2529   0.07825   0.06790  -0.1614   0.4568   1.0000
   8.750   1.2820   0.07766   0.06734  -0.1606   0.4548   1.0000
   9.250   1.2817   0.08457   0.07439  -0.1588   0.4397   1.0000
   9.750   1.2757   0.09250   0.08251  -0.1574   0.4245   1.0000
  10.000   1.3023   0.09218   0.08226  -0.1565   0.4224   1.0000
  10.500   1.2873   0.10167   0.09193  -0.1556   0.4067   1.0000
  11.000   1.2707   0.11148   0.10193  -0.1553   0.3911   1.0000
  11.250   1.2952   0.11148   0.10204  -0.1543   0.3887   1.0000
  11.750   1.2785   0.12133   0.11208  -0.1545   0.3729   1.0000
  12.000   1.3050   0.12093   0.11180  -0.1534   0.3707   1.0000
  12.500   1.2976   0.12898   0.12004  -0.1535   0.3546   1.0000
  12.750   1.2768   0.13565   0.12679  -0.1548   0.3429   1.0000
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