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FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: FX 76-MP-120 (fx76mp120-il)
Reynolds number: 500,000
Max Cl/Cd: 147.29 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx76mp120-il-500000.txt
Download as CSV file: xf-fx76mp120-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000   0.2056   0.08761   0.08410  -0.1620   0.8340   0.0225
  -9.750   0.2053   0.08470   0.08119  -0.1660   0.8309   0.0235
  -9.500   0.2119   0.08212   0.07863  -0.1671   0.8283   0.0236
  -9.250   0.2170   0.07870   0.07524  -0.1681   0.8258   0.0238
  -9.000   0.2307   0.07646   0.07299  -0.1679   0.8235   0.0242
  -8.750   0.2443   0.07472   0.07123  -0.1683   0.8212   0.0248
  -8.500   0.2545   0.07259   0.06909  -0.1694   0.8189   0.0252
  -8.250   0.2661   0.07062   0.06710  -0.1707   0.8163   0.0269
  -8.000   0.2658   0.06811   0.06465  -0.1720   0.8135   0.0286
  -7.750   0.2625   0.06521   0.06180  -0.1738   0.8099   0.0291
  -7.500   0.2655   0.06273   0.05934  -0.1743   0.8069   0.0292
  -7.250   0.2609   0.05930   0.05593  -0.1742   0.8041   0.0296
  -7.000   0.2695   0.05725   0.05386  -0.1746   0.8018   0.0299
  -6.750   0.2786   0.05558   0.05222  -0.1748   0.7993   0.0303
  -6.500   0.2888   0.05417   0.05084  -0.1747   0.7966   0.0312
  -6.250   0.2545   0.02085   0.01626  -0.2076   0.7901   0.0231
  -6.000   0.2808   0.01793   0.01277  -0.2097   0.7881   0.0243
  -5.750   0.3091   0.01765   0.01245  -0.2102   0.7863   0.0255
  -5.500   0.3356   0.01690   0.01154  -0.2105   0.7842   0.0267
  -5.250   0.3619   0.01591   0.01034  -0.2107   0.7819   0.0281
  -5.000   0.3892   0.01530   0.00952  -0.2109   0.7795   0.0292
  -4.750   0.4164   0.01436   0.00848  -0.2113   0.7772   0.0314
  -4.500   0.4448   0.01409   0.00814  -0.2116   0.7752   0.0336
  -4.250   0.4739   0.01375   0.00766  -0.2119   0.7733   0.0358
  -4.000   0.5029   0.01303   0.00685  -0.2125   0.7715   0.0387
  -3.750   0.5305   0.01291   0.00669  -0.2125   0.7693   0.0418
  -3.500   0.5569   0.01287   0.00662  -0.2123   0.7668   0.0445
  -3.250   0.5836   0.01232   0.00606  -0.2123   0.7641   0.0487
  -3.000   0.6116   0.01218   0.00588  -0.2124   0.7617   0.0526
  -2.750   0.6402   0.01183   0.00548  -0.2126   0.7594   0.0568
  -2.500   0.6696   0.01167   0.00529  -0.2130   0.7573   0.0618
  -2.250   0.6988   0.01162   0.00516  -0.2134   0.7551   0.0660
  -2.000   0.7241   0.01132   0.00492  -0.2130   0.7522   0.0723
  -1.750   0.7508   0.01124   0.00484  -0.2128   0.7493   0.0785
  -1.500   0.7786   0.01102   0.00463  -0.2129   0.7466   0.0868
  -1.250   0.8074   0.01092   0.00449  -0.2132   0.7441   0.0956
  -1.000   0.8369   0.01077   0.00434  -0.2136   0.7419   0.1089
  -0.750   0.8644   0.01069   0.00429  -0.2136   0.7393   0.1251
  -0.500   0.8896   0.01056   0.00427  -0.2132   0.7358   0.1481
  -0.250   0.9167   0.01040   0.00422  -0.2132   0.7325   0.1869
   0.000   0.9449   0.01018   0.00417  -0.2135   0.7295   0.2615
   0.250   0.9735   0.00986   0.00416  -0.2140   0.7269   0.4050
   0.500   0.9956   0.00936   0.00440  -0.2130   0.7237   0.7031
   0.750   1.0159   0.00922   0.00451  -0.2113   0.7198   0.8173
   1.000   1.0384   0.00911   0.00448  -0.2099   0.7162   0.8737
   1.250   1.0717   0.00889   0.00433  -0.2110   0.7132   0.9677
   1.500   1.0996   0.00894   0.00432  -0.2111   0.7099   1.0000
   1.750   1.1245   0.00899   0.00436  -0.2106   0.7055   1.0000
   2.000   1.1517   0.00901   0.00435  -0.2106   0.7014   1.0000
   2.250   1.1803   0.00903   0.00431  -0.2108   0.6977   1.0000
   2.500   1.2060   0.00910   0.00436  -0.2105   0.6932   1.0000
   2.750   1.2311   0.00914   0.00439  -0.2100   0.6880   1.0000
   3.000   1.2584   0.00917   0.00438  -0.2100   0.6836   1.0000
   3.250   1.2839   0.00924   0.00444  -0.2097   0.6785   1.0000
   3.500   1.3081   0.00930   0.00450  -0.2090   0.6726   1.0000
   3.750   1.3351   0.00936   0.00450  -0.2090   0.6675   1.0000
   4.000   1.3576   0.00944   0.00463  -0.2080   0.6608   1.0000
   4.250   1.3823   0.00952   0.00468  -0.2075   0.6545   1.0000
   4.500   1.4057   0.00963   0.00479  -0.2067   0.6477   1.0000
   4.750   1.4287   0.00973   0.00488  -0.2059   0.6402   1.0000
   5.000   1.4509   0.00986   0.00503  -0.2048   0.6322   1.0000
   5.250   1.4729   0.01000   0.00512  -0.2038   0.6235   1.0000
   5.500   1.4931   0.01016   0.00530  -0.2024   0.6140   1.0000
   5.750   1.5132   0.01034   0.00547  -0.2010   0.6047   1.0000
   6.000   1.5318   0.01056   0.00567  -0.1993   0.5944   1.0000
   6.250   1.5486   0.01078   0.00589  -0.1973   0.5839   1.0000
   6.500   1.5631   0.01104   0.00614  -0.1948   0.5728   1.0000
   6.750   1.5766   0.01136   0.00642  -0.1921   0.5609   1.0000
   7.000   1.5890   0.01173   0.00676  -0.1893   0.5486   1.0000
   7.250   1.6010   0.01212   0.00714  -0.1865   0.5357   1.0000
   7.500   1.6131   0.01256   0.00756  -0.1838   0.5235   1.0000
   7.750   1.6238   0.01307   0.00806  -0.1810   0.5107   1.0000
   8.000   1.6337   0.01365   0.00862  -0.1781   0.4981   1.0000
   8.250   1.6424   0.01433   0.00927  -0.1751   0.4848   1.0000
   8.500   1.6507   0.01508   0.00999  -0.1722   0.4720   1.0000
   8.750   1.6591   0.01590   0.01079  -0.1694   0.4584   1.0000
   9.000   1.6678   0.01676   0.01164  -0.1668   0.4449   1.0000
   9.250   1.6761   0.01770   0.01258  -0.1643   0.4314   1.0000
   9.500   1.6844   0.01871   0.01358  -0.1619   0.4182   1.0000
   9.750   1.6915   0.01983   0.01468  -0.1594   0.4041   1.0000
  10.000   1.6968   0.02110   0.01591  -0.1568   0.3884   1.0000
  10.250   1.7003   0.02253   0.01729  -0.1541   0.3710   1.0000
  10.500   1.7025   0.02409   0.01878  -0.1513   0.3528   1.0000
  10.750   1.7043   0.02573   0.02036  -0.1486   0.3337   1.0000
  11.000   1.7064   0.02741   0.02198  -0.1460   0.3139   1.0000
  11.250   1.7075   0.02921   0.02371  -0.1434   0.2948   1.0000
  11.500   1.7081   0.03110   0.02552  -0.1409   0.2767   1.0000
  11.750   1.7106   0.03291   0.02727  -0.1386   0.2592   1.0000
  12.000   1.7129   0.03478   0.02910  -0.1364   0.2422   1.0000
  12.250   1.7153   0.03670   0.03097  -0.1344   0.2256   1.0000
  12.500   1.7179   0.03865   0.03288  -0.1324   0.2105   1.0000
  12.750   1.7196   0.04072   0.03491  -0.1304   0.1952   1.0000
  13.000   1.7213   0.04282   0.03698  -0.1286   0.1803   1.0000
  13.250   1.7208   0.04520   0.03929  -0.1266   0.1643   1.0000
  13.500   1.7195   0.04771   0.04174  -0.1248   0.1481   1.0000
  13.750   1.7184   0.05024   0.04421  -0.1230   0.1320   1.0000
  14.000   1.7157   0.05301   0.04692  -0.1213   0.1152   1.0000
  14.250   1.7083   0.05634   0.05014  -0.1194   0.0955   1.0000
  14.500   1.7022   0.05962   0.05334  -0.1178   0.0775   1.0000
  14.750   1.6928   0.06337   0.05700  -0.1162   0.0603   1.0000
  15.000   1.6843   0.06715   0.06072  -0.1149   0.0455   1.0000
  15.250   1.6745   0.07124   0.06476  -0.1137   0.0336   1.0000
  15.500   1.6661   0.07527   0.06878  -0.1128   0.0250   1.0000
  15.750   1.6588   0.07929   0.07282  -0.1121   0.0199   1.0000
  16.000   1.6529   0.08325   0.07684  -0.1116   0.0168   1.0000
  16.250   1.6477   0.08723   0.08092  -0.1113   0.0148   1.0000
  16.500   1.6433   0.09115   0.08493  -0.1111   0.0133   1.0000
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