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FX 76-MP-120 (fx76mp120-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: FX 76-MP-120 (fx76mp120-il)
Reynolds number: 500,000
Max Cl/Cd: 141.45 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx76mp120-il-500000-n5.txt
Download as CSV file: xf-fx76mp120-il-500000-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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250   0.1597   0.08841   0.08464  -0.1525   0.7948   0.0106
 -10.000   0.1672   0.08554   0.08177  -0.1539   0.7927   0.0106
  -9.750   0.1737   0.08247   0.07871  -0.1554   0.7906   0.0108
  -9.500   0.1808   0.07958   0.07580  -0.1568   0.7885   0.0106
  -8.500   0.0051   0.02259   0.01819  -0.2004   0.7728   0.0125
  -8.250   0.0288   0.02067   0.01601  -0.2022   0.7709   0.0128
  -8.000   0.0533   0.01919   0.01431  -0.2033   0.7690   0.0132
  -7.750   0.0785   0.01792   0.01282  -0.2042   0.7670   0.0137
  -7.500   0.1045   0.01679   0.01147  -0.2049   0.7651   0.0142
  -7.250   0.1311   0.01587   0.01034  -0.2055   0.7630   0.0147
  -7.000   0.1581   0.01506   0.00934  -0.2060   0.7610   0.0153
  -6.750   0.1855   0.01453   0.00872  -0.2064   0.7591   0.0160
  -6.500   0.2134   0.01416   0.00826  -0.2068   0.7574   0.0169
  -6.250   0.2416   0.01371   0.00767  -0.2072   0.7558   0.0177
  -6.000   0.2691   0.01323   0.00708  -0.2075   0.7539   0.0185
  -5.750   0.2966   0.01276   0.00651  -0.2077   0.7517   0.0194
  -5.500   0.3242   0.01242   0.00612  -0.2079   0.7496   0.0204
  -5.250   0.3520   0.01217   0.00582  -0.2081   0.7475   0.0219
  -5.000   0.3800   0.01190   0.00547  -0.2082   0.7454   0.0234
  -4.750   0.4081   0.01159   0.00510  -0.2085   0.7434   0.0250
  -4.500   0.4365   0.01140   0.00485  -0.2087   0.7416   0.0268
  -4.250   0.4646   0.01121   0.00459  -0.2089   0.7396   0.0287
  -4.000   0.4921   0.01098   0.00436  -0.2090   0.7373   0.0309
  -3.750   0.5197   0.01084   0.00421  -0.2090   0.7349   0.0336
  -3.500   0.5474   0.01072   0.00404  -0.2091   0.7325   0.0359
  -3.250   0.5753   0.01053   0.00385  -0.2092   0.7302   0.0391
  -3.000   0.6034   0.01042   0.00370  -0.2093   0.7280   0.0424
  -2.750   0.6318   0.01031   0.00353  -0.2095   0.7258   0.0456
  -2.500   0.6589   0.01019   0.00344  -0.2095   0.7231   0.0497
  -2.250   0.6861   0.01010   0.00333  -0.2094   0.7201   0.0533
  -2.000   0.7135   0.00998   0.00322  -0.2094   0.7171   0.0581
  -1.750   0.7412   0.00990   0.00314  -0.2095   0.7144   0.0636
  -1.500   0.7691   0.00984   0.00303  -0.2096   0.7119   0.0690
  -1.250   0.7964   0.00977   0.00299  -0.2095   0.7090   0.0770
  -1.000   0.8233   0.00972   0.00296  -0.2094   0.7058   0.0849
  -0.750   0.8503   0.00967   0.00293  -0.2094   0.7025   0.0941
  -0.500   0.8775   0.00961   0.00289  -0.2093   0.6992   0.1070
  -0.250   0.9050   0.00957   0.00285  -0.2093   0.6961   0.1223
   0.000   0.9312   0.00953   0.00288  -0.2091   0.6921   0.1430
   0.250   0.9576   0.00947   0.00289  -0.2090   0.6880   0.1715
   0.500   0.9843   0.00941   0.00291  -0.2089   0.6843   0.2089
   0.750   1.0109   0.00933   0.00294  -0.2088   0.6807   0.2670
   1.000   1.0366   0.00921   0.00303  -0.2086   0.6761   0.3469
   1.250   1.0619   0.00898   0.00313  -0.2084   0.6714   0.5007
   1.500   1.0846   0.00868   0.00331  -0.2075   0.6673   0.7163
   1.750   1.1073   0.00864   0.00344  -0.2064   0.6624   0.7933
   2.000   1.1306   0.00865   0.00350  -0.2054   0.6570   0.8322
   2.250   1.1522   0.00863   0.00354  -0.2041   0.6520   0.8821
   2.500   1.1838   0.00856   0.00357  -0.2050   0.6459   1.0000
   2.750   1.2087   0.00867   0.00363  -0.2045   0.6392   1.0000
   3.000   1.2336   0.00879   0.00371  -0.2040   0.6326   1.0000
   3.250   1.2576   0.00892   0.00381  -0.2034   0.6252   1.0000
   3.500   1.2815   0.00906   0.00392  -0.2028   0.6175   1.0000
   3.750   1.3042   0.00922   0.00404  -0.2018   0.6090   1.0000
   4.000   1.3268   0.00938   0.00417  -0.2010   0.5997   1.0000
   4.250   1.3482   0.00958   0.00433  -0.1998   0.5906   1.0000
   4.500   1.3687   0.00979   0.00451  -0.1985   0.5802   1.0000
   4.750   1.3886   0.01001   0.00469  -0.1971   0.5696   1.0000
   5.000   1.4053   0.01026   0.00491  -0.1950   0.5585   1.0000
   5.250   1.4201   0.01057   0.00516  -0.1926   0.5460   1.0000
   5.500   1.4350   0.01090   0.00544  -0.1902   0.5337   1.0000
   5.750   1.4493   0.01126   0.00576  -0.1878   0.5204   1.0000
   6.000   1.4635   0.01164   0.00610  -0.1854   0.5079   1.0000
   6.250   1.4774   0.01205   0.00649  -0.1830   0.4964   1.0000
   6.500   1.4900   0.01253   0.00694  -0.1805   0.4845   1.0000
   6.750   1.5010   0.01309   0.00745  -0.1777   0.4715   1.0000
   7.000   1.5128   0.01367   0.00800  -0.1753   0.4588   1.0000
   7.250   1.5235   0.01434   0.00863  -0.1727   0.4451   1.0000
   7.500   1.5348   0.01503   0.00931  -0.1703   0.4324   1.0000
   7.750   1.5463   0.01576   0.01002  -0.1681   0.4209   1.0000
   8.000   1.5572   0.01657   0.01081  -0.1658   0.4095   1.0000
   8.250   1.5673   0.01747   0.01168  -0.1636   0.3969   1.0000
   8.500   1.5787   0.01834   0.01255  -0.1616   0.3847   1.0000
   8.750   1.5902   0.01925   0.01345  -0.1597   0.3736   1.0000
   9.000   1.5996   0.02031   0.01448  -0.1576   0.3607   1.0000
   9.250   1.6088   0.02141   0.01556  -0.1555   0.3481   1.0000
   9.500   1.6184   0.02251   0.01665  -0.1536   0.3366   1.0000
   9.750   1.6279   0.02364   0.01777  -0.1517   0.3238   1.0000
  10.000   1.6371   0.02481   0.01894  -0.1497   0.3117   1.0000
  10.250   1.6439   0.02617   0.02026  -0.1476   0.2972   1.0000
  10.500   1.6476   0.02777   0.02179  -0.1452   0.2793   1.0000
  10.750   1.6494   0.02954   0.02348  -0.1427   0.2604   1.0000
  11.000   1.6518   0.03133   0.02519  -0.1404   0.2401   1.0000
  11.250   1.6513   0.03338   0.02712  -0.1379   0.2182   1.0000
  11.500   1.6522   0.03538   0.02903  -0.1356   0.1973   1.0000
  11.750   1.6528   0.03748   0.03104  -0.1334   0.1777   1.0000
  12.000   1.6538   0.03959   0.03306  -0.1313   0.1599   1.0000
  12.250   1.6543   0.04180   0.03519  -0.1293   0.1410   1.0000
  12.500   1.6555   0.04401   0.03733  -0.1275   0.1249   1.0000
  12.750   1.6554   0.04638   0.03963  -0.1256   0.1086   1.0000
  13.000   1.6562   0.04875   0.04196  -0.1239   0.0948   1.0000
  13.250   1.6554   0.05131   0.04446  -0.1222   0.0795   1.0000
  13.500   1.6538   0.05403   0.04713  -0.1206   0.0654   1.0000
  13.750   1.6528   0.05676   0.04984  -0.1192   0.0540   1.0000
  14.000   1.6515   0.05959   0.05265  -0.1178   0.0438   1.0000
  14.250   1.6491   0.06260   0.05564  -0.1166   0.0345   1.0000
  14.500   1.6482   0.06553   0.05858  -0.1155   0.0278   1.0000
  14.750   1.6477   0.06849   0.06157  -0.1146   0.0224   1.0000
  15.000   1.6473   0.07149   0.06460  -0.1138   0.0184   1.0000
  15.250   1.6463   0.07464   0.06781  -0.1131   0.0153   1.0000
  15.500   1.6464   0.07769   0.07092  -0.1125   0.0129   1.0000
  15.750   1.6468   0.08076   0.07407  -0.1120   0.0114   1.0000
  16.000   1.6467   0.08398   0.07736  -0.1117   0.0101   1.0000
  16.500   1.6459   0.09061   0.08416  -0.1114   0.0083   1.0000
  16.750   1.6448   0.09410   0.08774  -0.1114   0.0076   1.0000
  17.000   1.6429   0.09775   0.09148  -0.1115   0.0071   1.0000
  17.250   1.6403   0.10156   0.09539  -0.1118   0.0067   1.0000
  17.500   1.6393   0.10517   0.09912  -0.1122   0.0064   1.0000
  17.750   1.6373   0.10898   0.10304  -0.1127   0.0060   1.0000
  18.000   1.6347   0.11291   0.10708  -0.1134   0.0057   1.0000
  18.250   1.6319   0.11692   0.11119  -0.1142   0.0055   1.0000
  18.500   1.6282   0.12107   0.11544  -0.1151   0.0052   1.0000
  18.750   1.6237   0.12541   0.11988  -0.1163   0.0050   1.0000
  19.000   1.6186   0.12990   0.12448  -0.1176   0.0049   1.0000
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