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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 100,000
Max Cl/Cd: 58.27 at α=6.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e211-il-100000.txt
Download as CSV file: xf-e211-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E211  (10.96%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4261   0.09718   0.09230  -0.0327   1.0000   0.1218
  -8.500  -0.4341   0.09430   0.08950  -0.0333   1.0000   0.1270
  -8.250  -0.4809   0.09198   0.08740  -0.0369   1.0000   0.1297
  -8.000  -0.4644   0.08775   0.08318  -0.0343   1.0000   0.1323
  -7.750  -0.4532   0.08518   0.08062  -0.0318   1.0000   0.1359
  -7.500  -0.4672   0.08268   0.07822  -0.0307   1.0000   0.1398
  -7.250  -0.5205   0.07652   0.07214  -0.0408   1.0000   0.1453
  -7.000  -0.4977   0.07459   0.07031  -0.0344   1.0000   0.1480
  -6.750  -0.4962   0.07182   0.06757  -0.0332   1.0000   0.1525
  -6.250  -0.5214   0.04578   0.04000  -0.0509   1.0000   0.0762
  -6.000  -0.5038   0.03892   0.03210  -0.0517   1.0000   0.0622
  -5.750  -0.4842   0.03592   0.02864  -0.0515   1.0000   0.0620
  -5.500  -0.4629   0.03327   0.02557  -0.0512   1.0000   0.0618
  -5.250  -0.4399   0.03115   0.02303  -0.0508   1.0000   0.0612
  -5.000  -0.4156   0.02858   0.02011  -0.0506   1.0000   0.0610
  -4.750  -0.3910   0.02659   0.01780  -0.0502   1.0000   0.0614
  -4.500  -0.3669   0.02438   0.01546  -0.0498   1.0000   0.0630
  -4.250  -0.3439   0.02305   0.01412  -0.0492   1.0000   0.0661
  -4.000  -0.3212   0.02220   0.01316  -0.0484   1.0000   0.0726
  -3.750  -0.2987   0.02109   0.01215  -0.0479   1.0000   0.0808
  -3.500  -0.2750   0.02000   0.01116  -0.0474   1.0000   0.0977
  -3.250  -0.2475   0.01811   0.00998  -0.0484   1.0000   0.2027
  -3.000  -0.2237   0.01664   0.01004  -0.0489   1.0000   0.4605
  -2.750  -0.2076   0.01692   0.01062  -0.0467   1.0000   0.5898
  -2.500  -0.1927   0.01732   0.01107  -0.0442   1.0000   0.6442
  -2.250  -0.1568   0.01801   0.01169  -0.0454   0.9914   0.6958
  -2.000  -0.1208   0.01858   0.01222  -0.0464   0.9817   0.7359
  -1.750  -0.0843   0.01902   0.01260  -0.0476   0.9723   0.7703
  -1.500  -0.0535   0.01918   0.01270  -0.0477   0.9610   0.7996
  -1.250  -0.0243   0.01924   0.01272  -0.0476   0.9499   0.8261
  -1.000   0.0041   0.01922   0.01267  -0.0472   0.9390   0.8515
  -0.750   0.0344   0.01914   0.01252  -0.0472   0.9291   0.8775
  -0.500   0.0676   0.01898   0.01232  -0.0477   0.9200   0.9050
  -0.250   0.1000   0.01878   0.01210  -0.0484   0.9090   0.9344
   0.000   0.1562   0.01867   0.01192  -0.0540   0.9021   0.9640
   0.250   0.2204   0.01849   0.01166  -0.0616   0.8945   0.9971
   0.500   0.2585   0.01833   0.01141  -0.0647   0.8837   1.0000
   0.750   0.3098   0.01802   0.01103  -0.0697   0.8774   1.0000
   1.000   0.3474   0.01788   0.01083  -0.0723   0.8660   1.0000
   1.250   0.3918   0.01763   0.01054  -0.0758   0.8573   1.0000
   1.500   0.4413   0.01728   0.01016  -0.0800   0.8501   1.0000
   1.750   0.4816   0.01712   0.01000  -0.0826   0.8394   1.0000
   2.000   0.5344   0.01664   0.00952  -0.0869   0.8333   1.0000
   2.250   0.5706   0.01655   0.00942  -0.0885   0.8208   1.0000
   2.500   0.6077   0.01646   0.00935  -0.0902   0.8085   1.0000
   2.750   0.6452   0.01635   0.00926  -0.0918   0.7960   1.0000
   3.000   0.6819   0.01627   0.00918  -0.0931   0.7827   1.0000
   3.250   0.7165   0.01623   0.00917  -0.0940   0.7682   1.0000
   3.500   0.7491   0.01625   0.00920  -0.0945   0.7526   1.0000
   3.750   0.7803   0.01631   0.00927  -0.0947   0.7363   1.0000
   4.000   0.8106   0.01639   0.00936  -0.0947   0.7194   1.0000
   4.250   0.8407   0.01648   0.00946  -0.0946   0.7020   1.0000
   4.500   0.8678   0.01663   0.00963  -0.0940   0.6832   1.0000
   4.750   0.8929   0.01681   0.00984  -0.0931   0.6630   1.0000
   5.000   0.9200   0.01694   0.00999  -0.0924   0.6430   1.0000
   5.250   0.9439   0.01713   0.01022  -0.0912   0.6213   1.0000
   5.500   0.9685   0.01728   0.01038  -0.0901   0.5987   1.0000
   5.750   0.9904   0.01746   0.01062  -0.0885   0.5739   1.0000
   6.000   1.0122   0.01763   0.01083  -0.0869   0.5473   1.0000
   6.250   1.0320   0.01780   0.01103  -0.0849   0.5170   1.0000
   6.500   1.0501   0.01802   0.01125  -0.0826   0.4825   1.0000
   6.750   1.0660   0.01833   0.01152  -0.0800   0.4419   1.0000
   7.000   1.0793   0.01881   0.01188  -0.0771   0.3929   1.0000
   7.250   1.0891   0.01961   0.01245  -0.0738   0.3335   1.0000
   7.500   1.0956   0.02082   0.01327  -0.0702   0.2690   1.0000
   7.750   1.1008   0.02230   0.01432  -0.0668   0.2120   1.0000
   8.000   1.1067   0.02380   0.01548  -0.0638   0.1642   1.0000
   8.250   1.1123   0.02545   0.01688  -0.0606   0.1266   1.0000
   8.500   1.1133   0.02740   0.01858  -0.0568   0.0947   1.0000
   8.750   1.1159   0.02950   0.02053  -0.0531   0.0717   1.0000
   9.000   1.1251   0.03163   0.02263  -0.0505   0.0608   1.0000
   9.250   1.1435   0.03415   0.02504  -0.0494   0.0544   1.0000
   9.500   1.1683   0.03636   0.02744  -0.0488   0.0497   1.0000
   9.750   1.1937   0.03893   0.02996  -0.0491   0.0456   1.0000
  10.000   1.2178   0.04196   0.03328  -0.0488   0.0431   1.0000
  10.250   1.2361   0.04490   0.03659  -0.0476   0.0419   1.0000
  10.500   1.2485   0.04816   0.04024  -0.0458   0.0413   1.0000
  10.750   1.2534   0.05150   0.04402  -0.0433   0.0410   1.0000
  11.000   1.2519   0.05487   0.04777  -0.0402   0.0411   1.0000
  11.250   1.2447   0.05835   0.05161  -0.0368   0.0413   1.0000
  11.500   1.2336   0.06195   0.05554  -0.0337   0.0416   1.0000
  11.750   1.2192   0.06572   0.05961  -0.0310   0.0419   1.0000
  12.000   1.2025   0.06976   0.06392  -0.0289   0.0423   1.0000
  12.250   1.1838   0.07415   0.06856  -0.0277   0.0426   1.0000
  12.500   1.1637   0.07899   0.07363  -0.0275   0.0429   1.0000
  12.750   1.1429   0.08433   0.07917  -0.0283   0.0433   1.0000
  13.000   1.1217   0.09023   0.08525  -0.0300   0.0437   1.0000
  13.250   1.1013   0.09670   0.09187  -0.0325   0.0441   1.0000
  13.500   0.9427   0.10106   0.09675  -0.0306   0.0446   1.0000
  13.750   0.9029   0.10840   0.10437  -0.0365   0.0455   1.0000
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