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E212 (10.55%) (e212-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E212 (10.55%) (e212-il)
Reynolds number: 50,000
Max Cl/Cd: 38.27 at α=6.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e212-il-50000.txt
Download as CSV file: xf-e212-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E212  (10.55%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4085   0.10798   0.10105  -0.0228   1.0000   0.2632
  -8.250  -0.3836   0.10255   0.09559  -0.0213   1.0000   0.2710
  -8.000  -0.4110   0.10250   0.09573  -0.0211   1.0000   0.2784
  -7.750  -0.3909   0.09729   0.09051  -0.0201   1.0000   0.2823
  -7.500  -0.3889   0.09428   0.08756  -0.0192   1.0000   0.2866
  -7.250  -0.4213   0.09407   0.08758  -0.0175   1.0000   0.2941
  -7.000  -0.4970   0.07136   0.06501  -0.0451   1.0000   0.1288
  -6.750  -0.5093   0.06237   0.05583  -0.0516   1.0000   0.1177
  -6.500  -0.5053   0.05649   0.04967  -0.0546   1.0000   0.1140
  -6.250  -0.4957   0.05100   0.04386  -0.0573   1.0000   0.1131
  -6.000  -0.4797   0.04555   0.03787  -0.0603   1.0000   0.1130
  -5.750  -0.4574   0.04060   0.03225  -0.0630   1.0000   0.1140
  -5.500  -0.4300   0.03630   0.02711  -0.0651   1.0000   0.1159
  -5.250  -0.4070   0.03370   0.02449  -0.0650   1.0000   0.1225
  -5.000  -0.3804   0.03123   0.02169  -0.0656   1.0000   0.1354
  -4.750  -0.3529   0.02904   0.01925  -0.0658   1.0000   0.1574
  -4.500  -0.3273   0.02749   0.01784  -0.0659   1.0000   0.2015
  -4.250  -0.3029   0.02647   0.01708  -0.0655   1.0000   0.2617
  -4.000  -0.2804   0.02574   0.01663  -0.0642   1.0000   0.3165
  -3.750  -0.2573   0.02516   0.01613  -0.0632   1.0000   0.3708
  -3.500  -0.2371   0.02482   0.01595  -0.0613   1.0000   0.4181
  -3.250  -0.2172   0.02454   0.01574  -0.0594   1.0000   0.4638
  -3.000  -0.1976   0.02432   0.01556  -0.0575   1.0000   0.5082
  -2.750  -0.1812   0.02419   0.01556  -0.0547   1.0000   0.5468
  -2.500  -0.1635   0.02404   0.01542  -0.0524   1.0000   0.5880
  -2.250  -0.1486   0.02393   0.01535  -0.0494   1.0000   0.6258
  -2.000  -0.1334   0.02382   0.01525  -0.0467   1.0000   0.6652
  -1.750  -0.1208   0.02371   0.01518  -0.0434   1.0000   0.7031
  -1.500  -0.1090   0.02358   0.01507  -0.0401   1.0000   0.7427
  -1.250  -0.0991   0.02341   0.01491  -0.0365   1.0000   0.7850
  -1.000  -0.0935   0.02314   0.01468  -0.0321   1.0000   0.8291
  -0.750  -0.0911   0.02267   0.01430  -0.0271   1.0000   0.8826
  -0.500  -0.0714   0.02174   0.01346  -0.0269   1.0000   0.9888
  -0.250  -0.0231   0.02197   0.01332  -0.0353   1.0000   1.0000
   0.000   0.0158   0.02247   0.01350  -0.0405   1.0000   1.0000
   0.250   0.0471   0.02308   0.01385  -0.0437   1.0000   1.0000
   0.500   0.0742   0.02375   0.01432  -0.0457   1.0000   1.0000
   0.750   0.0987   0.02449   0.01488  -0.0472   1.0000   1.0000
   1.000   0.1215   0.02529   0.01555  -0.0484   1.0000   1.0000
   1.250   0.1430   0.02616   0.01631  -0.0494   1.0000   1.0000
   1.500   0.1856   0.02753   0.01758  -0.0542   0.9888   1.0000
   1.750   0.2398   0.02902   0.01897  -0.0608   0.9717   1.0000
   2.000   0.2856   0.03010   0.02001  -0.0656   0.9532   1.0000
   2.250   0.3353   0.03116   0.02105  -0.0708   0.9353   1.0000
   2.500   0.3813   0.03206   0.02194  -0.0751   0.9172   1.0000
   2.750   0.4216   0.03280   0.02273  -0.0782   0.8977   1.0000
   3.000   0.4676   0.03344   0.02343  -0.0819   0.8788   1.0000
   3.250   0.5171   0.03392   0.02399  -0.0858   0.8609   1.0000
   3.500   0.5510   0.03443   0.02461  -0.0872   0.8397   1.0000
   3.750   0.5951   0.03468   0.02498  -0.0897   0.8201   1.0000
   4.000   0.6470   0.03451   0.02497  -0.0927   0.8018   1.0000
   4.250   0.6819   0.03467   0.02531  -0.0934   0.7799   1.0000
   4.500   0.7321   0.03403   0.02488  -0.0953   0.7601   1.0000
   4.750   0.7974   0.03249   0.02364  -0.0984   0.7416   1.0000
   5.000   0.8348   0.03204   0.02338  -0.0982   0.7171   1.0000
   5.250   0.8947   0.03027   0.02188  -0.0998   0.6940   1.0000
   5.500   0.9423   0.02906   0.02085  -0.0999   0.6659   1.0000
   5.750   0.9803   0.02840   0.02030  -0.0991   0.6339   1.0000
   6.000   1.0101   0.02821   0.02022  -0.0974   0.5986   1.0000
   6.250   1.0440   0.02787   0.01984  -0.0960   0.5609   1.0000
   6.500   1.0674   0.02815   0.02011  -0.0937   0.5208   1.0000
   6.750   1.0912   0.02851   0.02039  -0.0914   0.4791   1.0000
   7.000   1.1127   0.02910   0.02083  -0.0891   0.4358   1.0000
   7.250   1.1317   0.02993   0.02146  -0.0865   0.3921   1.0000
   7.500   1.1492   0.03099   0.02228  -0.0840   0.3488   1.0000
   7.750   1.1631   0.03237   0.02356  -0.0813   0.3077   1.0000
   8.000   1.1778   0.03398   0.02504  -0.0788   0.2691   1.0000
   8.250   1.1930   0.03577   0.02661  -0.0764   0.2328   1.0000
   8.500   1.2056   0.03781   0.02849  -0.0739   0.1989   1.0000
   8.750   1.2134   0.03974   0.03035  -0.0710   0.1681   1.0000
   9.000   1.2231   0.04202   0.03248  -0.0685   0.1415   1.0000
   9.250   1.2361   0.04486   0.03540  -0.0664   0.1218   1.0000
   9.500   1.2520   0.04828   0.03902  -0.0647   0.1094   1.0000
   9.750   1.2658   0.05177   0.04273  -0.0631   0.1010   1.0000
  10.000   1.2734   0.05526   0.04665  -0.0608   0.0956   1.0000
  10.250   1.2912   0.05943   0.05088  -0.0601   0.0915   1.0000
  10.500   1.2909   0.06400   0.05586  -0.0576   0.0903   1.0000
  10.750   1.2816   0.06822   0.06058  -0.0545   0.0899   1.0000
  11.000   1.2678   0.07248   0.06524  -0.0515   0.0897   1.0000
  11.250   1.2499   0.07660   0.06966  -0.0484   0.0898   1.0000
  11.500   1.2299   0.08096   0.07428  -0.0461   0.0900   1.0000
  11.750   1.2093   0.08576   0.07929  -0.0447   0.0903   1.0000
  12.000   1.1892   0.09109   0.08479  -0.0444   0.0907   1.0000
  12.250   1.0787   0.10471   0.09889  -0.0538   0.0994   1.0000
  12.500   1.0510   0.11461   0.10882  -0.0596   0.1019   1.0000
  12.750   1.0359   0.12348   0.11769  -0.0642   0.1033   1.0000
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