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FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 76-MP-120 (fx76mp120-il)
Reynolds number: 200,000
Max Cl/Cd: 85.94 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76mp120-il-200000.txt
Download as CSV file: xf-fx76mp120-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 76-MP-120                                    
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.1793   0.09609   0.09191  -0.1569   0.9157   0.0402
 -10.000   0.1925   0.09350   0.08930  -0.1597   0.9123   0.0420
  -9.750   0.1961   0.09232   0.08811  -0.1637   0.9076   0.0439
  -9.500   0.1921   0.09148   0.08731  -0.1647   0.9015   0.0442
  -9.250   0.1962   0.08968   0.08550  -0.1672   0.8969   0.0443
  -9.000   0.2150   0.08448   0.08028  -0.1672   0.8953   0.0451
  -8.750   0.2329   0.08160   0.07737  -0.1672   0.8930   0.0461
  -8.500   0.2358   0.08009   0.07589  -0.1656   0.8884   0.0469
  -8.250   0.2425   0.07825   0.07406  -0.1653   0.8842   0.0484
  -8.000   0.2505   0.07625   0.07205  -0.1662   0.8808   0.0501
  -7.750   0.2524   0.07461   0.07043  -0.1668   0.8769   0.0525
  -7.500   0.2406   0.07411   0.07001  -0.1649   0.8704   0.0535
  -7.250   0.2265   0.07374   0.06969  -0.1655   0.8647   0.0542
  -7.000   0.2174   0.07285   0.06885  -0.1658   0.8590   0.0544
  -6.750   0.2155   0.07114   0.06717  -0.1673   0.8532   0.0545
  -6.500   0.2258   0.06740   0.06345  -0.1614   0.8518   0.0560
  -6.250   0.2419   0.06569   0.06171  -0.1600   0.8497   0.0583
  -6.000   0.2478   0.06414   0.06016  -0.1603   0.8461   0.0606
  -5.750   0.2321   0.06392   0.06003  -0.1565   0.8386   0.0620
  -5.500   0.2587   0.05951   0.05539  -0.1749   0.8334   0.0664
  -5.000   0.2406   0.05615   0.05217  -0.1662   0.8214   0.0678
  -4.750   0.2585   0.05437   0.05040  -0.1650   0.8195   0.0697
  -4.500   0.2880   0.05156   0.04751  -0.1688   0.8179   0.0730
  -4.250   0.2537   0.05280   0.04883  -0.1598   0.8066   0.0729
  -4.000   0.3056   0.04647   0.04210  -0.1729   0.8046   0.0820
  -3.750   0.3632   0.03781   0.03271  -0.1837   0.8036   0.0653
  -3.500   0.4140   0.03098   0.02513  -0.1913   0.8028   0.0589
  -3.250   0.3627   0.04081   0.03600  -0.1755   0.7909   0.0974
  -3.000   0.4035   0.03793   0.03295  -0.1794   0.7896   0.1001
  -2.750   0.4814   0.02757   0.02064  -0.1906   0.7898   0.0682
  -2.500   0.5189   0.02671   0.01970  -0.1925   0.7885   0.0741
  -2.250   0.5587   0.02587   0.01853  -0.1943   0.7874   0.0803
  -2.000   0.5509   0.02651   0.01920  -0.1889   0.7780   0.0827
  -1.750   0.5829   0.02595   0.01858  -0.1897   0.7756   0.0889
  -1.500   0.6199   0.02517   0.01765  -0.1912   0.7741   0.0973
  -1.250   0.6580   0.02448   0.01693  -0.1928   0.7729   0.1069
  -1.000   0.6968   0.02372   0.01617  -0.1947   0.7719   0.1189
  -0.750   0.6857   0.02503   0.01750  -0.1885   0.7614   0.1226
  -0.500   0.7215   0.02446   0.01695  -0.1898   0.7597   0.1389
  -0.250   0.7598   0.02378   0.01633  -0.1915   0.7584   0.1617
   0.000   0.7997   0.02306   0.01574  -0.1935   0.7574   0.2013
   0.250   0.8390   0.02218   0.01528  -0.1957   0.7563   0.3206
   0.500   0.8288   0.02302   0.01673  -0.1898   0.7456   0.5023
   0.750   0.8565   0.02176   0.01632  -0.1884   0.7441   1.0000
   1.000   0.8969   0.02134   0.01573  -0.1903   0.7428   1.0000
   1.250   0.9370   0.02094   0.01517  -0.1922   0.7416   1.0000
   1.500   0.9777   0.02054   0.01464  -0.1943   0.7405   1.0000
   1.750   0.9726   0.02172   0.01584  -0.1891   0.7298   1.0000
   2.000   1.0123   0.02125   0.01527  -0.1909   0.7283   1.0000
   2.250   1.0529   0.02077   0.01470  -0.1929   0.7270   1.0000
   2.500   1.0947   0.02026   0.01410  -0.1952   0.7258   1.0000
   2.750   1.0912   0.02129   0.01518  -0.1901   0.7153   1.0000
   3.000   1.1314   0.02076   0.01459  -0.1920   0.7136   1.0000
   3.250   1.1731   0.02020   0.01396  -0.1942   0.7121   1.0000
   3.500   1.1767   0.02095   0.01475  -0.1902   0.7030   1.0000
   3.750   1.2143   0.02046   0.01423  -0.1917   0.7003   1.0000
   4.000   1.2565   0.01981   0.01354  -0.1940   0.6981   1.0000
   4.250   1.2717   0.02010   0.01385  -0.1918   0.6911   1.0000
   4.500   1.3013   0.01984   0.01360  -0.1920   0.6863   1.0000
   4.750   1.3431   0.01922   0.01294  -0.1942   0.6835   1.0000
   5.000   1.3585   0.01945   0.01321  -0.1920   0.6761   1.0000
   5.250   1.3900   0.01912   0.01289  -0.1925   0.6709   1.0000
   5.500   1.4331   0.01850   0.01224  -0.1951   0.6674   1.0000
   5.750   1.4400   0.01889   0.01270  -0.1913   0.6579   1.0000
   6.000   1.4805   0.01836   0.01215  -0.1934   0.6532   1.0000
   6.250   1.4895   0.01866   0.01253  -0.1900   0.6436   1.0000
   6.500   1.5302   0.01816   0.01199  -0.1922   0.6378   1.0000
   6.750   1.5367   0.01849   0.01239  -0.1883   0.6272   1.0000
   7.000   1.5580   0.01849   0.01240  -0.1870   0.6184   1.0000
   7.250   1.5828   0.01842   0.01235  -0.1863   0.6093   1.0000
   7.500   1.5911   0.01877   0.01274  -0.1828   0.5984   1.0000
   7.750   1.6092   0.01893   0.01291  -0.1811   0.5878   1.0000
   8.000   1.6328   0.01900   0.01297  -0.1803   0.5771   1.0000
   8.250   1.6434   0.01939   0.01338  -0.1774   0.5648   1.0000
   8.500   1.6522   0.01990   0.01391  -0.1743   0.5521   1.0000
   8.750   1.6634   0.02042   0.01445  -0.1716   0.5394   1.0000
   9.000   1.6756   0.02096   0.01499  -0.1692   0.5267   1.0000
   9.250   1.6877   0.02155   0.01558  -0.1669   0.5138   1.0000
   9.500   1.6982   0.02223   0.01624  -0.1644   0.5003   1.0000
   9.750   1.7088   0.02296   0.01695  -0.1620   0.4870   1.0000
  10.000   1.7154   0.02387   0.01786  -0.1591   0.4730   1.0000
  10.250   1.7200   0.02492   0.01893  -0.1561   0.4590   1.0000
  10.500   1.7248   0.02603   0.02007  -0.1532   0.4451   1.0000
  10.750   1.7291   0.02722   0.02129  -0.1504   0.4310   1.0000
  11.000   1.7320   0.02852   0.02259  -0.1475   0.4162   1.0000
  11.250   1.7333   0.02996   0.02403  -0.1445   0.4009   1.0000
  11.500   1.7335   0.03154   0.02559  -0.1415   0.3852   1.0000
  11.750   1.7319   0.03327   0.02729  -0.1385   0.3687   1.0000
  12.000   1.7295   0.03516   0.02914  -0.1356   0.3520   1.0000
  12.250   1.7271   0.03715   0.03111  -0.1328   0.3356   1.0000
  12.500   1.7246   0.03927   0.03323  -0.1303   0.3194   1.0000
  12.750   1.7228   0.04145   0.03543  -0.1279   0.3038   1.0000
  13.000   1.7213   0.04371   0.03770  -0.1257   0.2884   1.0000
  13.250   1.7191   0.04612   0.04011  -0.1237   0.2728   1.0000
  13.500   1.7166   0.04866   0.04266  -0.1217   0.2573   1.0000
  13.750   1.7138   0.05134   0.04535  -0.1199   0.2418   1.0000
  14.000   1.7106   0.05416   0.04817  -0.1183   0.2263   1.0000
  14.250   1.7067   0.05715   0.05116  -0.1167   0.2106   1.0000
  14.500   1.7016   0.06037   0.05437  -0.1153   0.1944   1.0000
  14.750   1.6952   0.06385   0.05784  -0.1140   0.1779   1.0000
  15.000   1.6869   0.06768   0.06164  -0.1129   0.1611   1.0000
  15.250   1.6793   0.07155   0.06551  -0.1119   0.1419   1.0000
  15.500   1.6664   0.07620   0.07007  -0.1111   0.1215   1.0000
  15.750   1.6520   0.08123   0.07500  -0.1106   0.0985   1.0000
  16.000   1.6338   0.08693   0.08058  -0.1103   0.0762   1.0000
  16.250   1.6146   0.09294   0.08648  -0.1103   0.0593   1.0000
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