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EPPLER 1210 AIRFOIL (e1210-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 1210 AIRFOIL (e1210-il)
Reynolds number: 100,000
Max Cl/Cd: 45.9 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e1210-il-100000-n5.txt
Download as CSV file: xf-e1210-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 1210 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.2313   0.10979   0.10473  -0.0362   1.0000   0.0475
 -10.500  -0.2352   0.10550   0.10049  -0.0377   1.0000   0.0482
 -10.250  -0.2418   0.10090   0.09596  -0.0394   1.0000   0.0497
 -10.000  -0.2346   0.09918   0.09432  -0.0392   1.0000   0.0509
  -9.750  -0.2364   0.09592   0.09115  -0.0400   1.0000   0.0524
  -9.500  -0.2467   0.09034   0.08564  -0.0427   0.9943   0.0537
  -9.250  -0.2303   0.08545   0.08077  -0.0486   0.9496   0.0557
  -9.000  -0.2122   0.07910   0.07433  -0.0576   0.9108   0.0588
  -8.750  -0.1989   0.07191   0.06703  -0.0674   0.8782   0.0615
  -8.500  -0.3449   0.03797   0.03197  -0.0988   0.8434   0.0663
  -8.250  -0.3092   0.03911   0.03322  -0.0984   0.8204   0.0680
  -8.000  -0.2960   0.03652   0.03024  -0.0994   0.7998   0.0709
  -7.750  -0.2835   0.03362   0.02685  -0.1001   0.7817   0.0740
  -7.500  -0.2601   0.03308   0.02618  -0.0997   0.7640   0.0764
  -7.250  -0.2448   0.03039   0.02288  -0.0999   0.7484   0.0805
  -7.000  -0.2191   0.03024   0.02273  -0.0994   0.7331   0.0826
  -6.750  -0.1963   0.02915   0.02132  -0.0991   0.7195   0.0861
  -6.500  -0.1740   0.02795   0.01982  -0.0988   0.7053   0.0894
  -6.250  -0.1489   0.02756   0.01934  -0.0983   0.6923   0.0922
  -6.000  -0.1256   0.02636   0.01768  -0.0979   0.6802   0.0966
  -5.750  -0.1005   0.02589   0.01717  -0.0974   0.6675   0.0992
  -5.500  -0.0750   0.02543   0.01653  -0.0968   0.6566   0.1027
  -5.250  -0.0503   0.02451   0.01524  -0.0964   0.6445   0.1071
  -5.000  -0.0244   0.02420   0.01492  -0.0959   0.6340   0.1099
  -4.750   0.0014   0.02375   0.01433  -0.0954   0.6227   0.1138
  -4.500   0.0274   0.02313   0.01338  -0.0949   0.6131   0.1183
  -4.250   0.0533   0.02280   0.01308  -0.0944   0.6021   0.1216
  -4.000   0.0797   0.02244   0.01255  -0.0939   0.5930   0.1259
  -3.750   0.1061   0.02200   0.01190  -0.0935   0.5828   0.1307
  -3.500   0.1324   0.02170   0.01156  -0.0929   0.5743   0.1345
  -3.250   0.1589   0.02141   0.01120  -0.0925   0.5642   0.1394
  -3.000   0.1857   0.02110   0.01067  -0.0920   0.5561   0.1444
  -2.750   0.2119   0.02083   0.01046  -0.0915   0.5468   0.1489
  -2.500   0.2385   0.02062   0.01013  -0.0910   0.5384   0.1546
  -2.250   0.2653   0.02039   0.00979  -0.0905   0.5303   0.1601
  -2.000   0.2915   0.02019   0.00962  -0.0900   0.5218   0.1658
  -1.750   0.3183   0.02004   0.00932  -0.0895   0.5148   0.1726
  -1.500   0.3445   0.01986   0.00919  -0.0890   0.5062   0.1791
  -1.250   0.3710   0.01974   0.00902  -0.0885   0.4989   0.1868
  -1.000   0.3974   0.01964   0.00887  -0.0880   0.4918   0.1952
  -0.750   0.4236   0.01954   0.00880  -0.0875   0.4840   0.2046
  -0.500   0.4500   0.01946   0.00866  -0.0870   0.4776   0.2154
  -0.250   0.4761   0.01941   0.00864  -0.0865   0.4703   0.2288
   0.000   0.5022   0.01934   0.00863  -0.0860   0.4634   0.2445
   0.250   0.5286   0.01930   0.00856  -0.0855   0.4577   0.2655
   0.750   0.5802   0.01920   0.00871  -0.0845   0.4440   0.3370
   1.000   0.6063   0.01908   0.00874  -0.0840   0.4387   0.4052
   1.250   0.6306   0.01893   0.00896  -0.0833   0.4323   0.5085
   1.500   0.6518   0.01863   0.00916  -0.0815   0.4263   0.6611
   1.750   0.6904   0.01820   0.00913  -0.0825   0.4205   1.0000
   2.000   0.7158   0.01849   0.00931  -0.0820   0.4145   1.0000
   2.250   0.7412   0.01876   0.00947  -0.0814   0.4086   1.0000
   2.500   0.7670   0.01903   0.00958  -0.0809   0.4036   1.0000
   2.750   0.7926   0.01934   0.00974  -0.0804   0.3987   1.0000
   3.000   0.8174   0.01966   0.01003  -0.0798   0.3929   1.0000
   3.250   0.8426   0.01997   0.01023  -0.0793   0.3877   1.0000
   3.500   0.8684   0.02027   0.01037  -0.0788   0.3835   1.0000
   3.750   0.8928   0.02065   0.01072  -0.0782   0.3785   1.0000
   4.000   0.9171   0.02101   0.01106  -0.0776   0.3733   1.0000
   4.250   0.9419   0.02134   0.01130  -0.0770   0.3687   1.0000
   4.500   0.9677   0.02168   0.01149  -0.0766   0.3650   1.0000
   4.750   0.9907   0.02213   0.01198  -0.0759   0.3602   1.0000
   5.000   1.0142   0.02255   0.01240  -0.0752   0.3556   1.0000
   5.250   1.0383   0.02293   0.01271  -0.0746   0.3514   1.0000
   5.500   1.0634   0.02329   0.01296  -0.0741   0.3478   1.0000
   5.750   1.0855   0.02380   0.01351  -0.0733   0.3435   1.0000
   6.000   1.1075   0.02430   0.01404  -0.0725   0.3391   1.0000
   6.250   1.1304   0.02476   0.01448  -0.0718   0.3354   1.0000
   6.500   1.1543   0.02517   0.01483  -0.0712   0.3320   1.0000
   6.750   1.1777   0.02566   0.01525  -0.0706   0.3287   1.0000
   7.000   1.1965   0.02629   0.01600  -0.0695   0.3245   1.0000
   7.250   1.2168   0.02686   0.01660  -0.0685   0.3205   1.0000
   7.500   1.2384   0.02736   0.01709  -0.0677   0.3171   1.0000
   7.750   1.2617   0.02783   0.01750  -0.0671   0.3143   1.0000
   8.000   1.2823   0.02846   0.01814  -0.0662   0.3113   1.0000
   8.250   1.2972   0.02926   0.01908  -0.0647   0.3076   1.0000
   8.500   1.3139   0.02996   0.01984  -0.0634   0.3040   1.0000
   8.750   1.3328   0.03056   0.02045  -0.0624   0.3008   1.0000
   9.000   1.3541   0.03107   0.02093  -0.0616   0.2981   1.0000
   9.250   1.3748   0.03171   0.02154  -0.0609   0.2956   1.0000
   9.500   1.3815   0.03282   0.02283  -0.0586   0.2924   1.0000
   9.750   1.3887   0.03383   0.02396  -0.0562   0.2893   1.0000
  10.000   1.3988   0.03471   0.02491  -0.0543   0.2863   1.0000
  10.250   1.4135   0.03544   0.02565  -0.0530   0.2836   1.0000
  10.500   1.4336   0.03601   0.02619  -0.0522   0.2812   1.0000
  10.750   1.4434   0.03708   0.02731  -0.0506   0.2788   1.0000
  11.000   1.4336   0.03907   0.02953  -0.0476   0.2759   1.0000
  11.250   1.4275   0.04112   0.03174  -0.0454   0.2730   1.0000
  11.500   1.4277   0.04294   0.03366  -0.0440   0.2703   1.0000
  11.750   1.4370   0.04422   0.03498  -0.0430   0.2678   1.0000
  12.000   1.4570   0.04482   0.03556  -0.0425   0.2656   1.0000
  12.250   1.4647   0.04636   0.03714  -0.0416   0.2633   1.0000
  12.500   1.3747   0.05656   0.04784  -0.0409   0.2584   1.0000
  12.750   1.2931   0.06889   0.06045  -0.0436   0.2522   1.0000
  13.000   1.3196   0.06853   0.06008  -0.0428   0.2508   1.0000
  13.250   1.3565   0.06692   0.05843  -0.0416   0.2498   1.0000
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