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FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 76-MP-120 (fx76mp120-il)
Reynolds number: 200,000
Max Cl/Cd: 88.55 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx76mp120-il-200000-n5.txt
Download as CSV file: xf-fx76mp120-il-200000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.1584   0.09525   0.09043  -0.1555   0.8419   0.0291
 -10.000   0.1647   0.09264   0.08783  -0.1567   0.8387   0.0292
  -9.750   0.1723   0.08982   0.08500  -0.1577   0.8358   0.0292
  -9.250   0.1928   0.08267   0.07779  -0.1590   0.8314   0.0235
  -9.000   0.2024   0.08051   0.07565  -0.1587   0.8287   0.0230
  -8.750   0.2097   0.07834   0.07350  -0.1589   0.8255   0.0225
  -8.500   0.2156   0.07597   0.07113  -0.1595   0.8223   0.0221
  -8.250   0.2206   0.07335   0.06851  -0.1603   0.8195   0.0219
  -8.000   0.2260   0.07073   0.06589  -0.1612   0.8172   0.0217
  -7.750   0.2273   0.06820   0.06340  -0.1615   0.8140   0.0218
  -7.500   0.2279   0.06588   0.06113  -0.1613   0.8104   0.0216
  -7.250   0.2252   0.06329   0.05858  -0.1614   0.8067   0.0225
  -7.000   0.2221   0.06067   0.05598  -0.1617   0.8036   0.0227
  -6.750   0.2237   0.05693   0.05224  -0.1648   0.8010   0.0232
  -6.500   0.2212   0.05285   0.04822  -0.1679   0.7966   0.0234
  -6.250   0.2270   0.04809   0.04344  -0.1732   0.7927   0.0234
  -6.000   0.2365   0.02932   0.02391  -0.1941   0.7886   0.0240
  -5.750   0.2636   0.02773   0.02210  -0.1962   0.7868   0.0249
  -5.500   0.2904   0.02553   0.01954  -0.1984   0.7846   0.0267
  -5.250   0.3161   0.02188   0.01508  -0.2006   0.7814   0.0290
  -5.000   0.3420   0.02078   0.01379  -0.2011   0.7787   0.0302
  -4.750   0.3690   0.02016   0.01303  -0.2015   0.7763   0.0317
  -4.500   0.3975   0.01943   0.01206  -0.2020   0.7742   0.0343
  -4.250   0.4268   0.01866   0.01105  -0.2027   0.7723   0.0371
  -4.000   0.4565   0.01823   0.01054  -0.2033   0.7707   0.0395
  -3.750   0.4804   0.01791   0.01010  -0.2028   0.7676   0.0426
  -3.500   0.5053   0.01752   0.00963  -0.2025   0.7644   0.0459
  -3.250   0.5319   0.01725   0.00933  -0.2024   0.7618   0.0490
  -3.000   0.5598   0.01699   0.00895  -0.2026   0.7595   0.0535
  -2.750   0.5889   0.01657   0.00848  -0.2030   0.7575   0.0574
  -2.500   0.6189   0.01633   0.00818  -0.2035   0.7558   0.0624
  -2.250   0.6419   0.01624   0.00805  -0.2027   0.7523   0.0670
  -2.000   0.6663   0.01608   0.00792  -0.2023   0.7488   0.0722
  -1.750   0.6932   0.01595   0.00775  -0.2022   0.7460   0.0791
  -1.500   0.7218   0.01571   0.00752  -0.2024   0.7436   0.0865
  -1.250   0.7518   0.01553   0.00727  -0.2029   0.7415   0.0960
  -1.000   0.7767   0.01547   0.00724  -0.2025   0.7382   0.1070
  -0.750   0.7996   0.01545   0.00729  -0.2017   0.7342   0.1192
  -0.500   0.8261   0.01536   0.00722  -0.2016   0.7310   0.1372
  -0.250   0.8549   0.01520   0.00710  -0.2019   0.7284   0.1617
   0.000   0.8853   0.01499   0.00698  -0.2025   0.7262   0.2031
   0.250   0.9065   0.01501   0.00717  -0.2015   0.7218   0.2572
   0.500   0.9303   0.01484   0.00730  -0.2011   0.7177   0.3593
   0.750   0.9547   0.01430   0.00743  -0.2005   0.7145   0.6186
   1.000   0.9771   0.01395   0.00742  -0.1989   0.7119   0.8130
   1.250   0.9950   0.01392   0.00751  -0.1967   0.7072   0.8947
   1.750   1.0496   0.01392   0.00743  -0.1967   0.6990   1.0000
   2.000   1.0807   0.01389   0.00729  -0.1973   0.6962   1.0000
   2.250   1.0985   0.01417   0.00759  -0.1956   0.6899   1.0000
   2.500   1.1246   0.01423   0.00760  -0.1953   0.6854   1.0000
   2.750   1.1550   0.01419   0.00749  -0.1959   0.6820   1.0000
   3.000   1.1733   0.01445   0.00777  -0.1942   0.6756   1.0000
   3.250   1.1983   0.01453   0.00782  -0.1938   0.6705   1.0000
   3.500   1.2273   0.01452   0.00776  -0.1940   0.6662   1.0000
   3.750   1.2442   0.01479   0.00807  -0.1921   0.6589   1.0000
   4.000   1.2715   0.01480   0.00803  -0.1921   0.6536   1.0000
   4.250   1.2902   0.01502   0.00827  -0.1905   0.6462   1.0000
   4.500   1.3145   0.01510   0.00834  -0.1899   0.6397   1.0000
   4.750   1.3338   0.01530   0.00855  -0.1884   0.6322   1.0000
   5.000   1.3559   0.01541   0.00864  -0.1874   0.6248   1.0000
   5.250   1.3724   0.01565   0.00889  -0.1853   0.6163   1.0000
   5.500   1.3955   0.01576   0.00898  -0.1845   0.6085   1.0000
   5.750   1.4096   0.01608   0.00933  -0.1821   0.5988   1.0000
   6.000   1.4290   0.01631   0.00955  -0.1807   0.5898   1.0000
   6.250   1.4470   0.01659   0.00981  -0.1790   0.5797   1.0000
   6.500   1.4616   0.01697   0.01021  -0.1769   0.5688   1.0000
   6.750   1.4776   0.01735   0.01057  -0.1750   0.5577   1.0000
   7.000   1.4934   0.01775   0.01095  -0.1731   0.5460   1.0000
   7.250   1.5077   0.01823   0.01141  -0.1710   0.5341   1.0000
   7.500   1.5202   0.01881   0.01200  -0.1687   0.5218   1.0000
   7.750   1.5327   0.01943   0.01261  -0.1665   0.5096   1.0000
   8.000   1.5450   0.02009   0.01326  -0.1643   0.4974   1.0000
   8.250   1.5563   0.02082   0.01398  -0.1621   0.4847   1.0000
   8.500   1.5671   0.02162   0.01476  -0.1598   0.4721   1.0000
   8.750   1.5766   0.02250   0.01565  -0.1575   0.4590   1.0000
   9.000   1.5860   0.02344   0.01660  -0.1552   0.4463   1.0000
   9.250   1.5954   0.02442   0.01758  -0.1530   0.4339   1.0000
   9.500   1.6042   0.02545   0.01862  -0.1508   0.4215   1.0000
   9.750   1.6125   0.02655   0.01972  -0.1486   0.4093   1.0000
  10.000   1.6199   0.02774   0.02092  -0.1464   0.3968   1.0000
  10.250   1.6272   0.02897   0.02217  -0.1443   0.3839   1.0000
  10.500   1.6342   0.03025   0.02348  -0.1421   0.3714   1.0000
  10.750   1.6405   0.03162   0.02486  -0.1400   0.3588   1.0000
  11.000   1.6466   0.03303   0.02629  -0.1379   0.3465   1.0000
  11.250   1.6512   0.03458   0.02784  -0.1358   0.3339   1.0000
  11.500   1.6548   0.03626   0.02954  -0.1337   0.3203   1.0000
  11.750   1.6573   0.03809   0.03136  -0.1315   0.3055   1.0000
  12.000   1.6580   0.04011   0.03337  -0.1294   0.2888   1.0000
  12.250   1.6580   0.04229   0.03552  -0.1273   0.2718   1.0000
  12.500   1.6568   0.04465   0.03784  -0.1253   0.2535   1.0000
  12.750   1.6547   0.04719   0.04033  -0.1233   0.2355   1.0000
  13.000   1.6523   0.04984   0.04294  -0.1215   0.2187   1.0000
  13.250   1.6507   0.05251   0.04560  -0.1199   0.2026   1.0000
  13.500   1.6497   0.05521   0.04829  -0.1185   0.1865   1.0000
  13.750   1.6479   0.05806   0.05112  -0.1171   0.1708   1.0000
  14.000   1.6453   0.06110   0.05413  -0.1158   0.1547   1.0000
  14.250   1.6415   0.06434   0.05734  -0.1147   0.1383   1.0000
  14.500   1.6367   0.06780   0.06076  -0.1137   0.1223   1.0000
  14.750   1.6314   0.07141   0.06434  -0.1128   0.1062   1.0000
  15.000   1.6252   0.07522   0.06811  -0.1120   0.0897   1.0000
  15.250   1.6180   0.07925   0.07211  -0.1114   0.0746   1.0000
  15.750   1.6023   0.08783   0.08065  -0.1108   0.0496   1.0000
  16.000   1.5953   0.09213   0.08496  -0.1108   0.0408   1.0000
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