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E211 (10.96%) (e211-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: E211 (10.96%) (e211-il)
Reynolds number: 500,000
Max Cl/Cd: 91.68 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e211-il-500000-n5.txt
Download as CSV file: xf-e211-il-500000-n5.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 =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.6411   0.05374   0.05126  -0.0559   1.0000   0.0083
 -10.000  -0.6702   0.04837   0.04578  -0.0582   1.0000   0.0083
  -9.750  -0.6868   0.04278   0.03996  -0.0639   0.9968   0.0083
  -9.500  -0.6784   0.03683   0.03354  -0.0702   0.9922   0.0083
  -9.250  -0.6619   0.03285   0.02915  -0.0736   0.9883   0.0084
  -9.000  -0.6366   0.03029   0.02621  -0.0764   0.9859   0.0086
  -8.750  -0.6146   0.02718   0.02271  -0.0785   0.9833   0.0087
  -8.500  -0.5956   0.02431   0.01950  -0.0791   0.9793   0.0089
  -8.250  -0.5696   0.02224   0.01718  -0.0804   0.9767   0.0090
  -8.000  -0.5404   0.02066   0.01539  -0.0818   0.9748   0.0092
  -7.750  -0.5097   0.01932   0.01388  -0.0834   0.9734   0.0093
  -7.500  -0.4832   0.01824   0.01267  -0.0838   0.9707   0.0095
  -7.250  -0.4592   0.01729   0.01161  -0.0835   0.9666   0.0097
  -7.000  -0.4300   0.01640   0.01061  -0.0843   0.9640   0.0099
  -6.750  -0.3989   0.01558   0.00969  -0.0855   0.9620   0.0102
  -6.500  -0.3665   0.01482   0.00883  -0.0868   0.9604   0.0106
  -6.250  -0.3432   0.01417   0.00812  -0.0862   0.9554   0.0108
  -6.000  -0.3151   0.01354   0.00742  -0.0865   0.9515   0.0112
  -5.750  -0.2837   0.01294   0.00675  -0.0875   0.9489   0.0115
  -5.500  -0.2506   0.01239   0.00615  -0.0888   0.9469   0.0119
  -5.250  -0.2287   0.01204   0.00574  -0.0877   0.9393   0.0123
  -5.000  -0.1980   0.01136   0.00500  -0.0885   0.9355   0.0131
  -4.750  -0.1706   0.01093   0.00453  -0.0885   0.9296   0.0137
  -4.500  -0.1417   0.01054   0.00409  -0.0888   0.9235   0.0145
  -4.250  -0.1081   0.01016   0.00366  -0.0900   0.9193   0.0156
  -4.000  -0.0776   0.00987   0.00331  -0.0906   0.9115   0.0168
  -3.750  -0.0392   0.00947   0.00293  -0.0929   0.9066   0.0225
  -3.500  -0.0022   0.00898   0.00260  -0.0951   0.8983   0.0602
  -3.250   0.0388   0.00848   0.00229  -0.0983   0.8900   0.1154
  -3.000   0.0780   0.00812   0.00204  -0.1009   0.8779   0.1602
  -2.750   0.1139   0.00777   0.00182  -0.1029   0.8626   0.2185
  -2.500   0.1459   0.00740   0.00164  -0.1041   0.8440   0.2960
  -2.250   0.1749   0.00692   0.00150  -0.1047   0.8244   0.4208
  -1.750   0.2303   0.00678   0.00147  -0.1047   0.7853   0.5300
  -1.500   0.2572   0.00683   0.00145  -0.1044   0.7664   0.5484
  -1.250   0.2839   0.00689   0.00144  -0.1040   0.7484   0.5654
  -1.000   0.3104   0.00696   0.00145  -0.1037   0.7314   0.5798
  -0.750   0.3370   0.00703   0.00145  -0.1034   0.7152   0.5920
  -0.500   0.3635   0.00710   0.00147  -0.1030   0.6997   0.6037
  -0.250   0.3900   0.00717   0.00149  -0.1027   0.6851   0.6145
   0.000   0.4166   0.00724   0.00152  -0.1024   0.6708   0.6249
   0.250   0.4433   0.00732   0.00156  -0.1021   0.6574   0.6354
   0.500   0.4699   0.00739   0.00161  -0.1018   0.6443   0.6455
   0.750   0.4965   0.00746   0.00166  -0.1015   0.6315   0.6554
   1.000   0.5232   0.00754   0.00172  -0.1012   0.6189   0.6655
   1.250   0.5496   0.00762   0.00179  -0.1009   0.6056   0.6747
   1.500   0.5759   0.00772   0.00186  -0.1006   0.5912   0.6830
   1.750   0.6021   0.00783   0.00194  -0.1002   0.5759   0.6914
   2.000   0.6282   0.00793   0.00203  -0.0998   0.5610   0.6994
   2.250   0.6545   0.00804   0.00212  -0.0995   0.5466   0.7083
   2.500   0.6804   0.00815   0.00222  -0.0991   0.5310   0.7172
   2.750   0.7061   0.00828   0.00233  -0.0987   0.5138   0.7266
   3.000   0.7316   0.00843   0.00246  -0.0982   0.4958   0.7367
   3.250   0.7569   0.00857   0.00259  -0.0977   0.4772   0.7478
   3.500   0.7821   0.00873   0.00274  -0.0971   0.4572   0.7595
   3.750   0.8067   0.00892   0.00291  -0.0965   0.4357   0.7721
   4.000   0.8315   0.00910   0.00308  -0.0959   0.4147   0.7860
   4.250   0.8554   0.00933   0.00328  -0.0952   0.3910   0.8016
   4.500   0.8779   0.00963   0.00351  -0.0942   0.3556   0.8195
   4.750   0.8978   0.01011   0.00381  -0.0927   0.3039   0.8399
   5.000   0.9148   0.01078   0.00421  -0.0908   0.2353   0.8645
   5.250   0.9311   0.01130   0.00457  -0.0886   0.1864   0.9011
   5.500   0.9534   0.01169   0.00487  -0.0877   0.1526   1.0000
   5.750   0.9761   0.01218   0.00524  -0.0869   0.1255   1.0000
   6.000   0.9974   0.01277   0.00567  -0.0860   0.0950   1.0000
   6.250   1.0194   0.01329   0.00608  -0.0851   0.0734   1.0000
   6.500   1.0408   0.01385   0.00653  -0.0841   0.0533   1.0000
   6.750   1.0609   0.01449   0.00704  -0.0830   0.0327   1.0000
   7.000   1.0800   0.01521   0.00765  -0.0816   0.0148   1.0000
   7.250   1.1007   0.01578   0.00821  -0.0805   0.0105   1.0000
   7.500   1.1217   0.01629   0.00875  -0.0794   0.0092   1.0000
   7.750   1.1419   0.01686   0.00937  -0.0781   0.0083   1.0000
   8.000   1.1624   0.01737   0.00995  -0.0770   0.0080   1.0000
   8.250   1.1820   0.01793   0.01059  -0.0756   0.0076   1.0000
   8.500   1.2006   0.01852   0.01125  -0.0742   0.0073   1.0000
   8.750   1.2174   0.01914   0.01194  -0.0724   0.0070   1.0000
   9.000   1.2330   0.01980   0.01267  -0.0705   0.0066   1.0000
   9.250   1.2477   0.02052   0.01345  -0.0684   0.0063   1.0000
   9.500   1.2608   0.02133   0.01433  -0.0662   0.0060   1.0000
   9.750   1.2710   0.02233   0.01541  -0.0636   0.0058   1.0000
  10.000   1.2787   0.02350   0.01669  -0.0607   0.0056   1.0000
  10.250   1.2881   0.02455   0.01783  -0.0582   0.0055   1.0000
  10.500   1.2981   0.02557   0.01894  -0.0559   0.0054   1.0000
  10.750   1.3072   0.02668   0.02015  -0.0536   0.0054   1.0000
  11.000   1.3158   0.02784   0.02141  -0.0514   0.0053   1.0000
  11.250   1.3220   0.02922   0.02290  -0.0490   0.0052   1.0000
  11.500   1.3286   0.03062   0.02440  -0.0469   0.0051   1.0000
  11.750   1.3332   0.03223   0.02613  -0.0448   0.0051   1.0000
  12.000   1.3381   0.03390   0.02793  -0.0430   0.0049   1.0000
  12.250   1.3412   0.03581   0.02996  -0.0413   0.0049   1.0000
  12.500   1.3438   0.03785   0.03212  -0.0397   0.0048   1.0000
  12.750   1.3454   0.04009   0.03450  -0.0384   0.0048   1.0000
  13.000   1.3464   0.04251   0.03705  -0.0374   0.0047   1.0000
  13.250   1.3462   0.04517   0.03985  -0.0366   0.0046   1.0000
  13.500   1.3453   0.04804   0.04286  -0.0361   0.0046   1.0000
  13.750   1.3433   0.05116   0.04613  -0.0358   0.0045   1.0000
  14.000   1.3403   0.05455   0.04967  -0.0359   0.0045   1.0000
  14.250   1.3359   0.05827   0.05355  -0.0363   0.0044   1.0000
  14.500   1.3307   0.06228   0.05771  -0.0370   0.0044   1.0000
  14.750   1.3243   0.06664   0.06223  -0.0381   0.0044   1.0000
  15.000   1.3165   0.07141   0.06716  -0.0396   0.0044   1.0000
  15.250   1.3081   0.07651   0.07241  -0.0415   0.0043   1.0000
  15.500   1.2981   0.08207   0.07814  -0.0437   0.0043   1.0000
  15.750   1.2871   0.08807   0.08431  -0.0465   0.0043   1.0000
  16.000   1.2751   0.09453   0.09093  -0.0496   0.0043   1.0000
  16.250   1.2622   0.10147   0.09804  -0.0532   0.0043   1.0000
  16.500   1.2483   0.10887   0.10560  -0.0573   0.0043   1.0000
  16.750   1.2336   0.11675   0.11365  -0.0618   0.0043   1.0000
  17.000   1.2181   0.12516   0.12223  -0.0668   0.0043   1.0000
  17.250   1.2023   0.13392   0.13114  -0.0721   0.0043   1.0000
  17.500   1.1855   0.14329   0.14067  -0.0779   0.0043   1.0000
  17.750   1.1679   0.15329   0.15083  -0.0842   0.0044   1.0000
  18.000   1.1476   0.16453   0.16222  -0.0912   0.0044   1.0000
  18.250   1.1215   0.17830   0.17616  -0.0997   0.0045   1.0000
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