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EPPLER 1211 AIRFOIL (e1211-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1211 AIRFOIL (e1211-il)
Reynolds number: 200,000
Max Cl/Cd: 62.56 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1211-il-200000-n5.txt
Download as CSV file: xf-e1211-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1211 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.5901   0.09139   0.08656  -0.0505   1.0000   0.0432
 -14.250  -0.6000   0.08655   0.08168  -0.0528   1.0000   0.0450
 -14.000  -0.6094   0.08197   0.07712  -0.0551   1.0000   0.0465
 -13.750  -0.6244   0.07669   0.07182  -0.0577   1.0000   0.0484
 -13.500  -0.6431   0.07124   0.06633  -0.0605   1.0000   0.0499
 -13.250  -0.6691   0.06516   0.06023  -0.0637   1.0000   0.0510
 -13.000  -0.7031   0.05832   0.05334  -0.0673   1.0000   0.0518
 -12.750  -0.7443   0.05098   0.04590  -0.0710   1.0000   0.0516
 -12.500  -0.7971   0.04256   0.03734  -0.0752   1.0000   0.0506
 -12.250  -0.8611   0.03364   0.02815  -0.0802   1.0000   0.0489
 -12.000  -0.8740   0.03080   0.02519  -0.0795   1.0000   0.0504
 -11.750  -0.8591   0.02853   0.02281  -0.0816   0.9955   0.0544
 -11.500  -0.8298   0.02659   0.02076  -0.0852   0.9854   0.0597
 -11.250  -0.8025   0.02509   0.01919  -0.0873   0.9715   0.0652
 -11.000  -0.7764   0.02387   0.01790  -0.0885   0.9533   0.0704
 -10.750  -0.7444   0.02280   0.01676  -0.0905   0.9367   0.0761
 -10.500  -0.7055   0.02184   0.01571  -0.0935   0.9212   0.0825
 -10.250  -0.6626   0.02099   0.01476  -0.0970   0.9038   0.0892
 -10.000  -0.6185   0.02025   0.01388  -0.1006   0.8835   0.0959
  -9.750  -0.5775   0.01965   0.01313  -0.1034   0.8594   0.1022
  -9.500  -0.5439   0.01921   0.01257  -0.1047   0.8342   0.1074
  -9.250  -0.5147   0.01886   0.01204  -0.1050   0.8107   0.1132
  -9.000  -0.4877   0.01864   0.01172  -0.1048   0.7890   0.1190
  -8.750  -0.4616   0.01845   0.01138  -0.1044   0.7696   0.1248
  -8.250  -0.4103   0.01814   0.01080  -0.1034   0.7344   0.1351
  -8.000  -0.3844   0.01803   0.01060  -0.1028   0.7189   0.1393
  -7.750  -0.3587   0.01784   0.01020  -0.1022   0.7043   0.1437
  -7.500  -0.3329   0.01766   0.00994  -0.1017   0.6898   0.1469
  -7.250  -0.3067   0.01753   0.00974  -0.1012   0.6765   0.1503
  -7.000  -0.2806   0.01739   0.00943  -0.1006   0.6639   0.1542
  -6.750  -0.2542   0.01718   0.00908  -0.1001   0.6512   0.1579
  -6.500  -0.2278   0.01707   0.00892  -0.0996   0.6397   0.1609
  -6.250  -0.2011   0.01696   0.00872  -0.0992   0.6276   0.1644
  -6.000  -0.1743   0.01683   0.00844  -0.0987   0.6168   0.1682
  -5.750  -0.1475   0.01666   0.00815  -0.0983   0.6057   0.1716
  -5.500  -0.1208   0.01654   0.00800  -0.0978   0.5955   0.1745
  -5.250  -0.0937   0.01644   0.00783  -0.0974   0.5849   0.1779
  -5.000  -0.0666   0.01634   0.00761  -0.0970   0.5755   0.1815
  -4.750  -0.0393   0.01623   0.00734  -0.0966   0.5654   0.1849
  -4.500  -0.0126   0.01608   0.00716  -0.0961   0.5563   0.1879
  -4.250   0.0148   0.01598   0.00704  -0.0958   0.5468   0.1910
  -4.000   0.0418   0.01592   0.00687  -0.0953   0.5382   0.1944
  -3.750   0.0694   0.01582   0.00670  -0.0950   0.5293   0.1980
  -3.500   0.0967   0.01576   0.00651  -0.0946   0.5205   0.2012
  -3.250   0.1238   0.01562   0.00637  -0.0942   0.5126   0.2043
  -3.000   0.1511   0.01555   0.00628  -0.0939   0.5042   0.2077
  -2.500   0.2059   0.01545   0.00605  -0.0932   0.4884   0.2149
  -2.250   0.2333   0.01543   0.00592  -0.0928   0.4806   0.2183
  -2.000   0.2602   0.01534   0.00584  -0.0924   0.4738   0.2219
  -1.750   0.2877   0.01529   0.00579  -0.0921   0.4663   0.2255
  -1.500   0.3148   0.01528   0.00572  -0.0917   0.4592   0.2294
  -1.250   0.3421   0.01528   0.00566  -0.0913   0.4522   0.2337
  -1.000   0.3695   0.01526   0.00561  -0.0909   0.4451   0.2375
  -0.750   0.3962   0.01524   0.00558  -0.0905   0.4388   0.2415
  -0.500   0.4235   0.01524   0.00558  -0.0902   0.4326   0.2461
  -0.250   0.4507   0.01526   0.00557  -0.0898   0.4258   0.2512
   0.000   0.4775   0.01531   0.00555  -0.0894   0.4195   0.2559
   0.250   0.5044   0.01530   0.00558  -0.0890   0.4136   0.2610
   0.500   0.5315   0.01533   0.00562  -0.0887   0.4076   0.2668
   0.750   0.5583   0.01540   0.00565  -0.0883   0.4018   0.2733
   1.000   0.5848   0.01545   0.00570  -0.0878   0.3965   0.2800
   1.250   0.6117   0.01549   0.00579  -0.0875   0.3905   0.2878
   1.500   0.6383   0.01557   0.00585  -0.0871   0.3848   0.2958
   1.750   0.6643   0.01565   0.00594  -0.0866   0.3801   0.3055
   2.000   0.6912   0.01573   0.00605  -0.0862   0.3750   0.3173
   2.250   0.7175   0.01579   0.00618  -0.0858   0.3695   0.3311
   2.500   0.7434   0.01588   0.00630  -0.0853   0.3645   0.3468
   2.750   0.7690   0.01600   0.00643  -0.0848   0.3601   0.3657
   3.000   0.7954   0.01606   0.00662  -0.0844   0.3554   0.3903
   3.250   0.8211   0.01613   0.00680  -0.0840   0.3506   0.4218
   3.500   0.8461   0.01621   0.00698  -0.0834   0.3460   0.4602
   3.750   0.8706   0.01631   0.00718  -0.0827   0.3420   0.5078
   4.000   0.8954   0.01633   0.00743  -0.0820   0.3376   0.5674
   4.250   0.9188   0.01632   0.00768  -0.0810   0.3335   0.6462
   4.500   0.9389   0.01627   0.00792  -0.0792   0.3297   0.7503
   4.750   0.9671   0.01616   0.00807  -0.0788   0.3257   1.0000
   5.000   0.9922   0.01643   0.00831  -0.0782   0.3219   1.0000
   5.250   1.0171   0.01668   0.00855  -0.0777   0.3177   1.0000
   5.500   1.0414   0.01696   0.00880  -0.0770   0.3138   1.0000
   5.750   1.0651   0.01727   0.00904  -0.0763   0.3104   1.0000
   6.000   1.0885   0.01762   0.00930  -0.0756   0.3073   1.0000
   6.250   1.1126   0.01790   0.00962  -0.0749   0.3038   1.0000
   6.500   1.1360   0.01820   0.00994  -0.0742   0.3000   1.0000
   6.750   1.1586   0.01852   0.01024  -0.0733   0.2964   1.0000
   7.000   1.1806   0.01888   0.01055  -0.0724   0.2932   1.0000
   7.250   1.2023   0.01928   0.01088  -0.0715   0.2903   1.0000
   7.500   1.2243   0.01962   0.01127  -0.0706   0.2873   1.0000
   7.750   1.2457   0.01998   0.01167  -0.0696   0.2842   1.0000
   8.000   1.2661   0.02036   0.01207  -0.0685   0.2810   1.0000
   8.250   1.2851   0.02075   0.01245  -0.0671   0.2780   1.0000
   8.500   1.3028   0.02118   0.01283  -0.0656   0.2752   1.0000
   8.750   1.3206   0.02163   0.01328  -0.0642   0.2726   1.0000
   9.000   1.3379   0.02207   0.01379  -0.0627   0.2698   1.0000
   9.250   1.3548   0.02255   0.01431  -0.0611   0.2671   1.0000
   9.500   1.3710   0.02305   0.01485  -0.0596   0.2644   1.0000
   9.750   1.3865   0.02358   0.01539  -0.0580   0.2619   1.0000
  10.000   1.4018   0.02415   0.01594  -0.0565   0.2594   1.0000
  10.250   1.4174   0.02477   0.01653  -0.0551   0.2570   1.0000
  10.500   1.4309   0.02542   0.01729  -0.0535   0.2545   1.0000
  10.750   1.4439   0.02613   0.01808  -0.0520   0.2518   1.0000
  11.000   1.4567   0.02688   0.01889  -0.0505   0.2495   1.0000
  11.250   1.4690   0.02768   0.01973  -0.0491   0.2471   1.0000
  11.500   1.4814   0.02851   0.02058  -0.0478   0.2450   1.0000
  11.750   1.4946   0.02936   0.02141  -0.0466   0.2429   1.0000
  12.000   1.5058   0.03034   0.02244  -0.0454   0.2407   1.0000
  12.250   1.5140   0.03151   0.02373  -0.0441   0.2383   1.0000
  12.500   1.5221   0.03273   0.02505  -0.0430   0.2358   1.0000
  12.750   1.5304   0.03400   0.02640  -0.0419   0.2336   1.0000
  13.000   1.5388   0.03530   0.02775  -0.0410   0.2314   1.0000
  13.250   1.5481   0.03657   0.02904  -0.0402   0.2292   1.0000
  13.500   1.5597   0.03773   0.03018  -0.0395   0.2272   1.0000
  13.750   1.5639   0.03949   0.03205  -0.0387   0.2251   1.0000
  14.000   1.5657   0.04151   0.03421  -0.0381   0.2227   1.0000
  14.250   1.5679   0.04357   0.03639  -0.0376   0.2204   1.0000
  14.500   1.5701   0.04568   0.03858  -0.0372   0.2179   1.0000
  14.750   1.5745   0.04762   0.04057  -0.0369   0.2156   1.0000
  15.000   1.5825   0.04924   0.04219  -0.0366   0.2135   1.0000
  15.250   1.5875   0.05123   0.04423  -0.0364   0.2114   1.0000
  15.500   1.5784   0.05479   0.04797  -0.0367   0.2088   1.0000
  15.750   1.5716   0.05824   0.05158  -0.0371   0.2062   1.0000
  16.000   1.5673   0.06151   0.05495  -0.0376   0.2036   1.0000
  16.250   1.5682   0.06422   0.05771  -0.0380   0.2012   1.0000
  16.500   1.5778   0.06588   0.05935  -0.0380   0.1991   1.0000
  16.750   1.5696   0.06988   0.06348  -0.0389   0.1966   1.0000
  17.000   1.5445   0.07632   0.07014  -0.0410   0.1934   1.0000
  17.250   1.5278   0.08183   0.07580  -0.0428   0.1903   1.0000
  17.500   1.5252   0.08540   0.07944  -0.0439   0.1877   1.0000
  17.750   1.5381   0.08672   0.08073  -0.0440   0.1857   1.0000
  18.000   1.5045   0.09509   0.08931  -0.0473   0.1821   1.0000
  18.250   1.4419   0.10843   0.10293  -0.0532   0.1766   1.0000
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