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GOE 243 (MVA PR.3) AIRFOIL (goe243-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: GOE 243 (MVA PR.3) AIRFOIL (goe243-il)
Reynolds number: 100,000
Max Cl/Cd: 44.6 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-goe243-il-100000.txt
Download as CSV file: xf-goe243-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: GOE 243 (MVA PR.3) 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
  ------ -------- --------- --------- -------- -------- --------
  -9.000   0.1194   0.11583   0.11087  -0.1059   0.8999   0.1272
  -8.750   0.1169   0.11492   0.11000  -0.1041   0.8905   0.1306
  -8.500   0.0887   0.11462   0.10976  -0.1086   0.8821   0.1357
  -8.250   0.1512   0.10840   0.10348  -0.1111   0.8819   0.1395
  -8.000   0.1610   0.10618   0.10124  -0.1170   0.8789   0.1485
  -7.750   0.1177   0.10757   0.10274  -0.1119   0.8630   0.1499
  -7.500   0.1858   0.10142   0.09652  -0.1144   0.8631   0.1548
  -7.250   0.1805   0.10093   0.09606  -0.1125   0.8535   0.1609
  -7.000   0.1708   0.09949   0.09467  -0.1126   0.8451   0.1662
  -6.750   0.2018   0.09660   0.09174  -0.1156   0.8425   0.1776
  -6.500   0.1431   0.09981   0.09508  -0.1075   0.8256   0.1789
  -6.250   0.2131   0.09371   0.08892  -0.1114   0.8259   0.1876
  -6.000   0.1852   0.09363   0.08888  -0.1109   0.8182   0.1964
  -5.750   0.1890   0.09288   0.08818  -0.1054   0.8070   0.1987
  -5.000   0.2080   0.05086   0.04444  -0.1852   0.7804   0.1102
  -4.750   0.1832   0.05181   0.04577  -0.1769   0.7658   0.1117
  -4.500   0.2657   0.04661   0.03984  -0.1902   0.7638   0.1026
  -4.250   0.3482   0.04313   0.03546  -0.2014   0.7625   0.0996
  -4.000   0.4071   0.04045   0.03269  -0.2062   0.7614   0.1016
  -3.750   0.4087   0.04123   0.03342  -0.2034   0.7479   0.1018
  -3.500   0.4601   0.03934   0.03135  -0.2065   0.7449   0.1024
  -3.250   0.5133   0.03740   0.02932  -0.2094   0.7430   0.1039
  -3.000   0.5617   0.03571   0.02760  -0.2113   0.7410   0.1064
  -2.750   0.5716   0.03640   0.02829  -0.2089   0.7295   0.1084
  -2.500   0.6067   0.03532   0.02740  -0.2088   0.7247   0.1137
  -2.250   0.6519   0.03401   0.02612  -0.2101   0.7219   0.1211
  -2.000   0.7070   0.03235   0.02452  -0.2138   0.7197   0.1333
  -1.750   0.7546   0.03136   0.02419  -0.2204   0.7098   0.2224
  -1.500   0.7809   0.03230   0.02539  -0.2178   0.7033   0.3759
  -1.250   0.8069   0.03297   0.02603  -0.2140   0.6996   0.4097
  -1.000   0.7983   0.03489   0.02815  -0.2065   0.6874   0.4163
  -0.750   0.8172   0.03554   0.02880  -0.2018   0.6820   0.4347
  -0.500   0.8425   0.03591   0.02912  -0.1977   0.6787   0.4549
  -0.250   0.8256   0.03785   0.03123  -0.1894   0.6655   0.4594
   0.000   0.8554   0.03774   0.03103  -0.1873   0.6612   0.4787
   0.250   0.9012   0.03707   0.03018  -0.1886   0.6582   0.4982
   0.500   0.8871   0.03849   0.03174  -0.1817   0.6451   0.5015
   0.750   0.9267   0.03754   0.03067  -0.1823   0.6409   0.5086
   1.000   0.9917   0.03593   0.02878  -0.1890   0.6377   0.5126
   1.250   1.0017   0.03693   0.02983  -0.1884   0.6255   0.5152
   1.500   1.0718   0.03528   0.02786  -0.1969   0.6206   0.5198
   1.750   1.1172   0.03416   0.02656  -0.1990   0.6162   0.5228
   2.000   1.1196   0.03517   0.02768  -0.1958   0.6044   0.5251
   2.250   1.1687   0.03404   0.02635  -0.1988   0.5992   0.5309
   2.500   1.1915   0.03449   0.02677  -0.1992   0.5899   0.5371
   2.750   1.2292   0.03405   0.02621  -0.2013   0.5825   0.5433
   3.000   1.2759   0.03310   0.02506  -0.2037   0.5777   0.5488
   3.250   1.2798   0.03421   0.02630  -0.2008   0.5676   0.5533
   3.500   1.3267   0.03360   0.02548  -0.2045   0.5611   0.5629
   3.750   1.3560   0.03353   0.02536  -0.2043   0.5555   0.5687
   4.000   1.3632   0.03456   0.02650  -0.2018   0.5472   0.5751
   4.250   1.4032   0.03423   0.02603  -0.2040   0.5416   0.5847
   4.500   1.4336   0.03421   0.02594  -0.2043   0.5357   0.5919
   4.750   1.4443   0.03515   0.02695  -0.2026   0.5272   0.6005
   5.000   1.4798   0.03471   0.02641  -0.2034   0.5215   0.6087
   5.250   1.5075   0.03512   0.02676  -0.2039   0.5153   0.6205
   5.500   1.5107   0.03601   0.02780  -0.2003   0.5078   0.6261
   5.750   1.5557   0.03543   0.02701  -0.2030   0.5016   0.6393
   6.000   1.5671   0.03605   0.02771  -0.2006   0.4947   0.6461
   6.250   1.5786   0.03684   0.02854  -0.1986   0.4874   0.6563
   6.500   1.6194   0.03631   0.02788  -0.2003   0.4819   0.6681
   6.750   1.6309   0.03722   0.02886  -0.1984   0.4758   0.6778
   7.000   1.6279   0.03836   0.03014  -0.1942   0.4692   0.6852
   7.250   1.6703   0.03799   0.02963  -0.1964   0.4635   0.6982
   7.500   1.6907   0.03857   0.03020  -0.1956   0.4576   0.7099
   7.750   1.6761   0.04026   0.03209  -0.1901   0.4509   0.7159
   8.000   1.7121   0.03997   0.03168  -0.1912   0.4448   0.7293
   8.250   1.7376   0.04029   0.03194  -0.1911   0.4387   0.7414
   8.500   1.7172   0.04251   0.03438  -0.1854   0.4316   0.7471
   8.750   1.7560   0.04194   0.03367  -0.1867   0.4250   0.7611
   9.000   1.7652   0.04292   0.03467  -0.1847   0.4184   0.7711
   9.250   1.7502   0.04509   0.03701  -0.1801   0.4108   0.7777
   9.500   1.8083   0.04339   0.03501  -0.1833   0.4036   0.7948
   9.750   1.7705   0.04689   0.03882  -0.1765   0.3959   0.7987
  10.000   1.7904   0.04707   0.03895  -0.1757   0.3877   0.8109
  10.250   1.7942   0.04840   0.04031  -0.1734   0.3795   0.8214
  10.500   1.7886   0.05021   0.04221  -0.1704   0.3704   0.8311
  10.750   1.8032   0.05076   0.04273  -0.1691   0.3617   0.8460
  11.000   1.7909   0.05321   0.04532  -0.1658   0.3520   0.8592
  11.250   1.7976   0.05407   0.04619  -0.1638   0.3434   1.0000
  11.500   1.7873   0.05692   0.04910  -0.1613   0.3338   1.0000
  11.750   1.8014   0.05804   0.05012  -0.1604   0.3258   1.0000
  12.000   1.7848   0.06174   0.05395  -0.1579   0.3172   1.0000
  12.250   1.8376   0.05976   0.05162  -0.1592   0.3112   1.0000
  12.500   1.7826   0.06706   0.05933  -0.1551   0.3040   1.0000
  12.750   1.7952   0.06848   0.06071  -0.1544   0.2985   1.0000
  13.000   1.8462   0.06651   0.05846  -0.1553   0.2945   1.0000
  13.250   1.7882   0.07489   0.06727  -0.1521   0.2895   1.0000
  13.500   1.7503   0.08204   0.07467  -0.1505   0.2847   1.0000
  13.750   1.7643   0.08347   0.07609  -0.1501   0.2815   1.0000
  14.000   1.8096   0.08143   0.07388  -0.1501   0.2791   1.0000
  14.250   1.8225   0.08321   0.07567  -0.1496   0.2765   1.0000
  14.500   1.1598   0.21992   0.21416  -0.2006   0.3124   0.8315
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