Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

Eiffel 371 (Monge) (eiffel371-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: Eiffel 371 (Monge) (eiffel371-il)
Reynolds number: 1,000,000
Max Cl/Cd: 80.69 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eiffel371-il-1000000-n5.txt
Download as CSV file: xf-eiffel371-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 371 (Monge)                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.8500   0.04921   0.04663  -0.0845   1.0000   0.0049
 -14.500  -0.8770   0.04231   0.03953  -0.0893   1.0000   0.0048
 -14.250  -0.8967   0.03853   0.03559  -0.0889   1.0000   0.0049
 -14.000  -0.9122   0.03577   0.03269  -0.0869   1.0000   0.0049
 -13.750  -0.9183   0.03407   0.03090  -0.0845   1.0000   0.0050
 -13.500  -0.9377   0.03190   0.02858  -0.0804   1.0000   0.0049
 -13.250  -0.9278   0.02967   0.02616  -0.0808   0.9981   0.0050
 -13.000  -0.9071   0.02854   0.02495  -0.0811   0.9956   0.0051
 -12.750  -0.8954   0.02680   0.02303  -0.0805   0.9913   0.0051
 -12.500  -0.8775   0.02543   0.02152  -0.0802   0.9870   0.0051
 -12.250  -0.8586   0.02426   0.02022  -0.0796   0.9825   0.0052
 -12.000  -0.8435   0.02295   0.01875  -0.0783   0.9766   0.0053
 -11.750  -0.8190   0.02203   0.01773  -0.0783   0.9739   0.0053
 -11.500  -0.8031   0.02066   0.01620  -0.0770   0.9671   0.0055
 -11.250  -0.7768   0.01952   0.01494  -0.0774   0.9630   0.0056
 -11.000  -0.7468   0.01859   0.01392  -0.0784   0.9596   0.0057
 -10.750  -0.7202   0.01776   0.01300  -0.0785   0.9538   0.0058
 -10.500  -0.6889   0.01720   0.01238  -0.0794   0.9496   0.0060
 -10.250  -0.6575   0.01655   0.01165  -0.0803   0.9453   0.0062
 -10.000  -0.6306   0.01592   0.01095  -0.0802   0.9379   0.0063
  -9.750  -0.6003   0.01537   0.01031  -0.0808   0.9309   0.0064
  -9.500  -0.5751   0.01484   0.00971  -0.0804   0.9220   0.0066
  -9.000  -0.5262   0.01392   0.00861  -0.0789   0.9046   0.0069
  -8.750  -0.5025   0.01349   0.00809  -0.0780   0.8960   0.0071
  -8.500  -0.4803   0.01313   0.00766  -0.0767   0.8862   0.0072
  -8.250  -0.4573   0.01280   0.00726  -0.0755   0.8763   0.0074
  -8.000  -0.4352   0.01246   0.00683  -0.0742   0.8639   0.0076
  -7.750  -0.4145   0.01205   0.00632  -0.0726   0.8487   0.0080
  -7.500  -0.3929   0.01178   0.00598  -0.0711   0.8299   0.0083
  -7.250  -0.3718   0.01158   0.00568  -0.0695   0.8037   0.0086
  -7.000  -0.3521   0.01145   0.00540  -0.0676   0.7709   0.0089
  -6.750  -0.3323   0.01134   0.00514  -0.0657   0.7395   0.0094
  -6.500  -0.3112   0.01125   0.00492  -0.0641   0.7142   0.0099
  -6.250  -0.2896   0.01110   0.00467  -0.0626   0.6930   0.0101
  -6.000  -0.2681   0.01090   0.00438  -0.0612   0.6738   0.0109
  -5.750  -0.2457   0.01074   0.00415  -0.0599   0.6570   0.0114
  -5.500  -0.2227   0.01060   0.00394  -0.0587   0.6418   0.0121
  -5.250  -0.1992   0.01048   0.00375  -0.0576   0.6294   0.0129
  -5.000  -0.1755   0.01037   0.00357  -0.0566   0.6168   0.0136
  -4.750  -0.1521   0.01022   0.00338  -0.0555   0.6038   0.0153
  -4.500  -0.1284   0.01012   0.00322  -0.0545   0.5902   0.0170
  -4.250  -0.1045   0.01002   0.00307  -0.0535   0.5777   0.0188
  -4.000  -0.0807   0.00992   0.00293  -0.0525   0.5666   0.0218
  -3.750  -0.0562   0.00981   0.00280  -0.0517   0.5563   0.0255
  -3.500  -0.0319   0.00972   0.00268  -0.0509   0.5477   0.0297
  -3.250  -0.0073   0.00959   0.00256  -0.0501   0.5404   0.0374
  -2.750   0.0410   0.00931   0.00237  -0.0484   0.5287   0.0716
  -2.500   0.0657   0.00920   0.00229  -0.0477   0.5225   0.0860
  -2.000   0.1133   0.00891   0.00215  -0.0460   0.5116   0.1429
  -1.750   0.1354   0.00867   0.00207  -0.0448   0.5058   0.1960
  -1.250   0.1712   0.00790   0.00193  -0.0409   0.4953   0.3982
  -1.000   0.1925   0.00770   0.00189  -0.0396   0.4898   0.4493
  -0.750   0.2163   0.00765   0.00197  -0.0387   0.4826   0.5060
  -0.500   0.2434   0.00770   0.00199  -0.0386   0.4757   0.5226
  -0.250   0.2696   0.00779   0.00200  -0.0382   0.4635   0.5303
   0.000   0.2958   0.00786   0.00203  -0.0379   0.4523   0.5374
   0.250   0.3225   0.00794   0.00205  -0.0376   0.4415   0.5427
   0.500   0.3485   0.00801   0.00207  -0.0373   0.4316   0.5478
   0.750   0.3743   0.00811   0.00211  -0.0369   0.4187   0.5523
   1.000   0.4000   0.00824   0.00215  -0.0366   0.4029   0.5567
   1.250   0.4249   0.00838   0.00220  -0.0361   0.3844   0.5594
   1.500   0.4493   0.00851   0.00224  -0.0355   0.3684   0.5607
   1.750   0.4738   0.00864   0.00230  -0.0350   0.3532   0.5620
   2.250   0.5234   0.00889   0.00244  -0.0340   0.3294   0.5650
   2.500   0.5482   0.00902   0.00251  -0.0336   0.3198   0.5666
   2.750   0.5724   0.00918   0.00260  -0.0331   0.3076   0.5683
   3.000   0.5972   0.00930   0.00269  -0.0327   0.2976   0.5695
   3.250   0.6217   0.00944   0.00278  -0.0323   0.2894   0.5704
   3.500   0.6468   0.00954   0.00285  -0.0320   0.2828   0.5712
   3.750   0.6711   0.00969   0.00296  -0.0315   0.2750   0.5721
   4.000   0.6957   0.00979   0.00305  -0.0311   0.2685   0.5734
   4.250   0.7190   0.00994   0.00315  -0.0305   0.2591   0.5749
   4.500   0.7430   0.01005   0.00326  -0.0301   0.2522   0.5760
   4.750   0.7665   0.01019   0.00337  -0.0295   0.2448   0.5771
   5.000   0.7900   0.01032   0.00349  -0.0290   0.2384   0.5784
   5.250   0.8131   0.01047   0.00362  -0.0284   0.2308   0.5800
   5.500   0.8355   0.01065   0.00376  -0.0277   0.2221   0.5815
   5.750   0.8575   0.01083   0.00391  -0.0270   0.2133   0.5830
   6.000   0.8790   0.01100   0.00407  -0.0261   0.2058   0.5841
   6.250   0.8984   0.01121   0.00423  -0.0249   0.1960   0.5848
   6.500   0.9183   0.01138   0.00439  -0.0237   0.1881   0.5854
   6.750   0.9366   0.01163   0.00459  -0.0223   0.1773   0.5860
   7.250   0.9697   0.01227   0.00512  -0.0189   0.1504   0.5875
   7.500   0.9875   0.01255   0.00538  -0.0174   0.1421   0.5885
   7.750   1.0036   0.01290   0.00569  -0.0158   0.1324   0.5894
   8.000   1.0200   0.01324   0.00600  -0.0142   0.1253   0.5905
   8.250   1.0375   0.01354   0.00630  -0.0128   0.1198   0.5914
   8.500   1.0561   0.01379   0.00657  -0.0117   0.1177   0.5926
   8.750   1.0729   0.01410   0.00688  -0.0103   0.1141   0.5938
   9.000   1.0889   0.01446   0.00724  -0.0087   0.1092   0.5952
   9.250   1.1067   0.01474   0.00755  -0.0076   0.1072   0.5968
   9.500   1.1242   0.01503   0.00787  -0.0064   0.1037   0.5983
   9.750   1.1403   0.01539   0.00823  -0.0051   0.1001   0.5997
  10.250   1.1701   0.01620   0.00907  -0.0022   0.0913   0.6042
  10.500   1.1682   0.01733   0.00999   0.0017   0.0631   0.6067
  11.000   1.1526   0.02036   0.01281   0.0104   0.0165   0.6130
  11.250   1.1611   0.02101   0.01362   0.0123   0.0136   0.6530
  11.500   1.1690   0.02186   0.01463   0.0141   0.0119   0.7311
  11.750   1.1775   0.02280   0.01563   0.0157   0.0102   0.7345
  12.000   1.1875   0.02369   0.01658   0.0169   0.0097   0.7372
  12.250   1.1961   0.02471   0.01764   0.0182   0.0089   0.7398
  12.500   1.2032   0.02588   0.01885   0.0194   0.0081   0.7413
  12.750   1.2104   0.02710   0.02012   0.0205   0.0077   0.7426
  13.000   1.2182   0.02834   0.02141   0.0214   0.0073   0.7436
  13.250   1.2245   0.02974   0.02287   0.0222   0.0070   0.7445
  13.500   1.2301   0.03125   0.02445   0.0230   0.0067   0.7454
  13.750   1.2353   0.03287   0.02612   0.0236   0.0064   0.7463
  14.000   1.2379   0.03477   0.02809   0.0242   0.0059   0.7472
  14.250   1.2398   0.03681   0.03020   0.0247   0.0057   0.7481
  14.500   1.2451   0.03862   0.03207   0.0249   0.0053   0.7489
  14.750   1.2474   0.04076   0.03429   0.0250   0.0053   0.7496
  15.000   1.2488   0.04305   0.03666   0.0251   0.0051   0.7504
  15.250   1.2490   0.04554   0.03922   0.0250   0.0050   0.7509
  15.500   1.2509   0.04791   0.04165   0.0248   0.0048   0.7515
  15.750   1.2477   0.05090   0.04472   0.0246   0.0046   0.7522
  16.000   1.2491   0.05342   0.04731   0.0242   0.0046   0.7527
  16.250   1.2435   0.05683   0.05081   0.0237   0.0044   0.7532
  16.500   1.2379   0.06034   0.05439   0.0230   0.0041   0.7536
  16.750   1.2363   0.06346   0.05760   0.0222   0.0041   0.7540
  17.000   1.2291   0.06735   0.06158   0.0213   0.0039   0.7543
  17.250   1.2225   0.07129   0.06561   0.0202   0.0040   0.7547
  17.500   1.2191   0.07492   0.06932   0.0190   0.0038   0.7550
  17.750   1.2080   0.07968   0.07420   0.0175   0.0039   0.7552
  18.000   1.1988   0.08432   0.07893   0.0159   0.0038   0.7554
  18.250   1.1935   0.08847   0.08317   0.0144   0.0036   0.7558
  18.500   1.1817   0.09373   0.08853   0.0124   0.0037   0.7559
  18.750   1.1688   0.09923   0.09414   0.0103   0.0037   0.7561
<< Back to Eiffel 371 (Monge) (eiffel371-il)

Polar data table (+)

Polar graphs


<< Back to Eiffel 371 (Monge) (eiffel371-il)