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E474 (14.09%) (e474-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E474 (14.09%) (e474-il)
Reynolds number: 100,000
Max Cl/Cd: 28.58 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e474-il-100000.txt
Download as CSV file: xf-e474-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E474  (14.09%)                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.6521   0.09194   0.08575  -0.0139   1.0000   0.1961
 -10.750  -0.6567   0.08724   0.08106  -0.0150   1.0000   0.1992
 -10.500  -0.9351   0.05134   0.04494  -0.0269   1.0000   0.1918
 -10.250  -0.9773   0.04609   0.03924  -0.0221   1.0000   0.1951
 -10.000  -0.9830   0.04340   0.03631  -0.0190   1.0000   0.1991
  -9.750  -0.9454   0.04426   0.03738  -0.0191   1.0000   0.2038
  -9.500  -0.9467   0.04208   0.03496  -0.0161   1.0000   0.2086
  -9.250  -0.9610   0.03896   0.03132  -0.0117   1.0000   0.2134
  -9.000  -0.9304   0.03887   0.03146  -0.0115   1.0000   0.2176
  -8.750  -0.9148   0.03798   0.03050  -0.0097   1.0000   0.2227
  -8.500  -0.9178   0.03573   0.02776  -0.0060   1.0000   0.2282
  -8.250  -0.8973   0.03476   0.02687  -0.0049   1.0000   0.2324
  -8.000  -0.8767   0.03418   0.02631  -0.0036   1.0000   0.2373
  -7.750  -0.8683   0.03270   0.02452  -0.0009   1.0000   0.2430
  -7.500  -0.8532   0.03142   0.02312   0.0009   1.0000   0.2476
  -7.250  -0.8317   0.03083   0.02259   0.0021   1.0000   0.2524
  -7.000  -0.8172   0.02980   0.02135   0.0041   1.0000   0.2583
  -6.750  -0.8021   0.02860   0.01996   0.0061   1.0000   0.2634
  -6.500  -0.7807   0.02794   0.01936   0.0072   1.0000   0.2680
  -6.250  -0.7627   0.02715   0.01845   0.0089   1.0000   0.2739
  -6.000  -0.7461   0.02616   0.01725   0.0107   1.0000   0.2795
  -5.750  -0.7246   0.02552   0.01667   0.0118   1.0000   0.2844
  -5.500  -0.7050   0.02482   0.01588   0.0133   1.0000   0.2901
  -5.250  -0.6865   0.02402   0.01491   0.0148   1.0000   0.2961
  -5.000  -0.6649   0.02346   0.01443   0.0159   1.0000   0.3014
  -4.750  -0.6448   0.02287   0.01375   0.0173   1.0000   0.3077
  -4.500  -0.6245   0.02219   0.01299   0.0186   1.0000   0.3134
  -4.250  -0.6030   0.02171   0.01257   0.0197   1.0000   0.3193
  -4.000  -0.5828   0.02124   0.01198   0.0210   1.0000   0.3265
  -3.750  -0.5613   0.02070   0.01151   0.0221   1.0000   0.3324
  -3.500  -0.5403   0.02029   0.01112   0.0233   1.0000   0.3390
  -3.250  -0.5198   0.01988   0.01064   0.0244   1.0000   0.3463
  -3.000  -0.4986   0.01952   0.01041   0.0255   1.0000   0.3533
  -2.750  -0.4785   0.01926   0.01005   0.0267   1.0000   0.3617
  -2.500  -0.4577   0.01891   0.00988   0.0277   1.0000   0.3686
  -2.250  -0.4385   0.01872   0.00967   0.0289   1.0000   0.3778
  -2.000  -0.4106   0.01850   0.00963   0.0283   0.9969   0.3872
  -1.750  -0.3461   0.01834   0.00961   0.0210   0.9803   0.4037
  -1.500  -0.2871   0.01792   0.00937   0.0151   0.9608   0.4219
  -1.250  -0.2281   0.01739   0.00904   0.0095   0.9409   0.4445
  -1.000  -0.1714   0.01665   0.00859   0.0048   0.9189   0.4701
  -0.750  -0.1222   0.01582   0.00806   0.0018   0.8893   0.5026
  -0.500  -0.0818   0.01497   0.00752   0.0009   0.8432   0.5425
  -0.250  -0.0348   0.01413   0.00693  -0.0007   0.7738   0.6035
   0.000   0.0000   0.01384   0.00668   0.0000   0.6820   0.6820
   0.250   0.0348   0.01413   0.00693   0.0008   0.6033   0.7738
   0.500   0.0818   0.01497   0.00752  -0.0009   0.5422   0.8432
   0.750   0.1222   0.01582   0.00806  -0.0018   0.5024   0.8893
   1.000   0.1713   0.01665   0.00859  -0.0048   0.4699   0.9188
   1.250   0.2280   0.01739   0.00903  -0.0095   0.4446   0.9409
   1.500   0.2870   0.01792   0.00937  -0.0151   0.4219   0.9608
   1.750   0.3460   0.01833   0.00961  -0.0210   0.4037   0.9803
   2.000   0.4107   0.01850   0.00962  -0.0284   0.3874   0.9970
   2.250   0.4384   0.01872   0.00967  -0.0289   0.3778   1.0000
   2.500   0.4577   0.01891   0.00987  -0.0277   0.3687   1.0000
   2.750   0.4784   0.01926   0.01005  -0.0267   0.3617   1.0000
   3.000   0.4985   0.01952   0.01040  -0.0255   0.3532   1.0000
   3.250   0.5197   0.01988   0.01064  -0.0244   0.3463   1.0000
   3.500   0.5402   0.02029   0.01111  -0.0232   0.3390   1.0000
   3.750   0.5612   0.02070   0.01151  -0.0221   0.3323   1.0000
   4.000   0.5827   0.02124   0.01198  -0.0210   0.3265   1.0000
   4.250   0.6029   0.02171   0.01257  -0.0197   0.3193   1.0000
   4.500   0.6244   0.02219   0.01299  -0.0186   0.3134   1.0000
   4.750   0.6447   0.02287   0.01375  -0.0173   0.3077   1.0000
   5.000   0.6648   0.02346   0.01443  -0.0159   0.3014   1.0000
   5.250   0.6864   0.02402   0.01491  -0.0148   0.2961   1.0000
   5.500   0.7050   0.02482   0.01588  -0.0133   0.2902   1.0000
   5.750   0.7245   0.02551   0.01667  -0.0118   0.2844   1.0000
   6.000   0.7461   0.02616   0.01725  -0.0107   0.2795   1.0000
   6.250   0.7627   0.02715   0.01844  -0.0089   0.2739   1.0000
   6.500   0.7806   0.02793   0.01935  -0.0072   0.2680   1.0000
   6.750   0.8021   0.02860   0.01996  -0.0061   0.2634   1.0000
   7.000   0.8171   0.02980   0.02134  -0.0041   0.2583   1.0000
   7.250   0.8317   0.03083   0.02259  -0.0021   0.2524   1.0000
   7.500   0.8531   0.03142   0.02312  -0.0009   0.2476   1.0000
   7.750   0.8683   0.03270   0.02451   0.0009   0.2431   1.0000
   8.000   0.8767   0.03418   0.02630   0.0036   0.2374   1.0000
   8.250   0.8974   0.03475   0.02686   0.0049   0.2324   1.0000
   8.500   0.9179   0.03572   0.02776   0.0060   0.2282   1.0000
   8.750   0.9148   0.03799   0.03051   0.0097   0.2228   1.0000
   9.000   0.9303   0.03887   0.03146   0.0115   0.2176   1.0000
   9.250   0.9610   0.03895   0.03131   0.0117   0.2134   1.0000
   9.500   0.9467   0.04209   0.03497   0.0161   0.2087   1.0000
   9.750   0.9457   0.04423   0.03735   0.0190   0.2038   1.0000
  10.000   0.9831   0.04340   0.03631   0.0190   0.1991   1.0000
  10.250   0.9778   0.04607   0.03921   0.0221   0.1951   1.0000
  10.500   0.9348   0.05140   0.04499   0.0269   0.1918   1.0000
  10.750   0.7534   0.07093   0.06483   0.0267   0.1949   1.0000
  11.000   0.9080   0.05687   0.05069   0.0323   0.1853   1.0000
  11.250   0.8565   0.06315   0.05707   0.0340   0.1840   1.0000
  11.500   0.8018   0.07289   0.06687   0.0304   0.1825   1.0000
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