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MA409 (original) (modified line 7) (ma409-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: MA409 (original) (modified line 7) (ma409-il)
Reynolds number: 1,000,000
Max Cl/Cd: 94.83 at α=1.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ma409-il-1000000-n5.txt
Download as CSV file: xf-ma409-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: MA409 (original)                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.4414   0.08661   0.08392  -0.0334   0.7068   0.0024
  -9.750  -0.4510   0.07911   0.07646  -0.0377   0.7066   0.0024
  -9.250  -0.4751   0.02671   0.02326  -0.0973   0.7068   0.0021
  -9.000  -0.4520   0.02261   0.01869  -0.1002   0.7062   0.0022
  -8.750  -0.4274   0.02017   0.01590  -0.1014   0.7053   0.0022
  -8.500  -0.4035   0.01719   0.01245  -0.1026   0.7044   0.0024
  -8.250  -0.3773   0.01623   0.01133  -0.1028   0.7034   0.0025
  -8.000  -0.3507   0.01542   0.01038  -0.1030   0.7026   0.0027
  -7.750  -0.3239   0.01444   0.00921  -0.1032   0.7020   0.0028
  -7.500  -0.2970   0.01343   0.00800  -0.1033   0.7012   0.0030
  -7.250  -0.2698   0.01258   0.00699  -0.1034   0.7004   0.0032
  -7.000  -0.2423   0.01186   0.00613  -0.1034   0.6995   0.0034
  -6.750  -0.2147   0.01129   0.00543  -0.1034   0.6984   0.0037
  -6.500  -0.1870   0.01085   0.00489  -0.1034   0.6976   0.0039
  -6.250  -0.1593   0.01019   0.00410  -0.1034   0.6968   0.0044
  -6.000  -0.1315   0.00982   0.00365  -0.1034   0.6959   0.0049
  -5.750  -0.1036   0.00953   0.00331  -0.1034   0.6950   0.0056
  -5.500  -0.0757   0.00929   0.00302  -0.1034   0.6937   0.0063
  -5.250  -0.0477   0.00892   0.00255  -0.1034   0.6920   0.0077
  -5.000  -0.0198   0.00867   0.00223  -0.1034   0.6902   0.0095
  -4.750   0.0083   0.00849   0.00198  -0.1034   0.6887   0.0117
  -4.500   0.0363   0.00813   0.00172  -0.1034   0.6868   0.0345
  -4.250   0.0645   0.00795   0.00160  -0.1035   0.6843   0.0485
  -4.000   0.0926   0.00781   0.00149  -0.1035   0.6803   0.0575
  -3.750   0.1208   0.00772   0.00140  -0.1035   0.6753   0.0616
  -3.500   0.1483   0.00760   0.00114  -0.1034   0.6063   0.0660
  -3.250   0.1743   0.00772   0.00110  -0.1031   0.5787   0.0709
  -2.750   0.2294   0.00772   0.00100  -0.1029   0.5680   0.0754
  -2.500   0.2572   0.00769   0.00095  -0.1029   0.5648   0.0789
  -2.250   0.2849   0.00766   0.00091  -0.1028   0.5613   0.0844
  -2.000   0.3124   0.00766   0.00091  -0.1028   0.5572   0.0913
  -1.750   0.3401   0.00757   0.00090  -0.1028   0.5523   0.1176
  -1.500   0.3677   0.00752   0.00091  -0.1028   0.5460   0.1443
  -1.250   0.3953   0.00750   0.00092  -0.1027   0.5409   0.1634
  -1.000   0.4232   0.00739   0.00093  -0.1028   0.5355   0.1978
  -0.750   0.4508   0.00728   0.00097  -0.1029   0.5269   0.2586
  -0.500   0.4787   0.00722   0.00098  -0.1029   0.5110   0.2891
  -0.250   0.5060   0.00724   0.00099  -0.1029   0.4832   0.3128
   0.000   0.5328   0.00732   0.00104  -0.1027   0.4601   0.3380
   0.250   0.5597   0.00737   0.00112  -0.1026   0.4431   0.3725
   0.500   0.5867   0.00738   0.00122  -0.1026   0.4263   0.4265
   0.750   0.6126   0.00754   0.00133  -0.1023   0.3839   0.4606
   1.000   0.6375   0.00755   0.00152  -0.1021   0.3433   0.5992
   1.250   0.6597   0.00696   0.00171  -0.1009   0.3129   1.0000
   1.500   0.6856   0.00723   0.00185  -0.1006   0.2766   1.0000
   1.750   0.7078   0.00798   0.00215  -0.0998   0.1770   1.0000
   2.000   0.7311   0.00862   0.00244  -0.0992   0.1013   1.0000
   2.250   0.7538   0.00938   0.00284  -0.0984   0.0225   1.0000
   2.500   0.7800   0.00964   0.00307  -0.0981   0.0122   1.0000
   2.750   0.8064   0.00986   0.00333  -0.0979   0.0100   1.0000
   3.000   0.8322   0.01019   0.00369  -0.0975   0.0074   1.0000
   3.250   0.8583   0.01045   0.00397  -0.0972   0.0063   1.0000
   3.500   0.8840   0.01075   0.00429  -0.0969   0.0055   1.0000
   3.750   0.9094   0.01110   0.00467  -0.0965   0.0048   1.0000
   4.000   0.9337   0.01165   0.00528  -0.0958   0.0042   1.0000
   4.250   0.9586   0.01207   0.00576  -0.0953   0.0039   1.0000
   4.500   0.9835   0.01247   0.00620  -0.0949   0.0035   1.0000
   4.750   1.0084   0.01285   0.00660  -0.0944   0.0031   1.0000
   5.000   1.0326   0.01333   0.00711  -0.0939   0.0028   1.0000
   5.250   1.0555   0.01400   0.00783  -0.0931   0.0026   1.0000
   5.500   1.0768   0.01491   0.00887  -0.0920   0.0024   1.0000
   5.750   1.0993   0.01562   0.00966  -0.0911   0.0023   1.0000
   6.000   1.1205   0.01651   0.01066  -0.0900   0.0022   1.0000
   6.250   1.1407   0.01760   0.01187  -0.0887   0.0020   1.0000
   6.500   1.1600   0.01891   0.01332  -0.0872   0.0019   1.0000
   6.750   1.1786   0.02050   0.01508  -0.0856   0.0018   1.0000
   7.000   1.1960   0.02259   0.01738  -0.0837   0.0017   1.0000
   7.250   1.2112   0.02568   0.02079  -0.0814   0.0017   1.0000
   7.500   1.2233   0.02943   0.02493  -0.0785   0.0017   1.0000
   7.750   1.2359   0.03201   0.02778  -0.0763   0.0016   1.0000
   8.000   1.2481   0.03407   0.03005  -0.0742   0.0016   1.0000
   8.250   1.2590   0.03601   0.03219  -0.0722   0.0015   1.0000
   8.500   1.2670   0.03811   0.03450  -0.0698   0.0014   1.0000
   8.750   1.2723   0.04021   0.03680  -0.0673   0.0014   1.0000
   9.000   1.2700   0.04315   0.04003  -0.0639   0.0014   1.0000
   9.250   1.2578   0.04632   0.04343  -0.0594   0.0013   1.0000
   9.500   1.2397   0.04969   0.04702  -0.0548   0.0013   1.0000
   9.750   1.2212   0.05333   0.05086  -0.0513   0.0013   1.0000
  10.000   1.2019   0.05747   0.05519  -0.0492   0.0013   1.0000
  10.250   1.1825   0.06225   0.06016  -0.0488   0.0013   1.0000
  10.500   1.1637   0.06782   0.06588  -0.0501   0.0013   1.0000
  10.750   1.1440   0.07430   0.07251  -0.0529   0.0013   1.0000
  11.000   1.1242   0.08270   0.08103  -0.0585   0.0013   1.0000
  11.250   1.1022   0.09325   0.09172  -0.0659   0.0014   1.0000
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