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EH 2.0/12 (eh2012-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/12 (eh2012-il)
Reynolds number: 200,000
Max Cl/Cd: 63.06 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2012-il-200000-n5.txt
Download as CSV file: xf-eh2012-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/12                                       
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.7360   0.05783   0.05415  -0.0339   1.0000   0.0140
 -11.000  -0.7659   0.05155   0.04764  -0.0366   1.0000   0.0138
 -10.750  -0.7951   0.04660   0.04241  -0.0357   1.0000   0.0137
 -10.500  -0.8144   0.04312   0.03866  -0.0328   1.0000   0.0138
 -10.250  -0.8260   0.03988   0.03506  -0.0298   1.0000   0.0141
 -10.000  -0.8297   0.03675   0.03152  -0.0272   1.0000   0.0145
  -9.750  -0.8262   0.03412   0.02847  -0.0249   1.0000   0.0148
  -9.500  -0.8186   0.03178   0.02585  -0.0230   1.0000   0.0152
  -9.250  -0.8061   0.03003   0.02392  -0.0214   1.0000   0.0156
  -9.000  -0.7912   0.02851   0.02224  -0.0199   1.0000   0.0160
  -8.750  -0.7749   0.02713   0.02069  -0.0185   1.0000   0.0165
  -8.500  -0.7576   0.02578   0.01917  -0.0172   1.0000   0.0171
  -8.250  -0.7395   0.02445   0.01766  -0.0158   1.0000   0.0178
  -8.000  -0.7207   0.02320   0.01623  -0.0145   1.0000   0.0185
  -7.750  -0.7013   0.02206   0.01489  -0.0131   1.0000   0.0194
  -7.500  -0.6829   0.02101   0.01376  -0.0117   1.0000   0.0205
  -7.250  -0.6633   0.02034   0.01307  -0.0105   1.0000   0.0219
  -7.000  -0.6438   0.01969   0.01235  -0.0091   0.9999   0.0237
  -6.750  -0.6089   0.01869   0.01121  -0.0109   0.9809   0.0260
  -6.500  -0.5747   0.01783   0.01033  -0.0126   0.9583   0.0288
  -6.250  -0.5397   0.01718   0.00954  -0.0142   0.9337   0.0327
  -6.000  -0.5077   0.01651   0.00884  -0.0152   0.9073   0.0375
  -5.750  -0.4790   0.01604   0.00822  -0.0152   0.8798   0.0424
  -5.500  -0.4539   0.01557   0.00770  -0.0146   0.8535   0.0487
  -5.250  -0.4298   0.01519   0.00719  -0.0137   0.8286   0.0549
  -5.000  -0.4060   0.01487   0.00678  -0.0127   0.8063   0.0625
  -4.750  -0.3824   0.01454   0.00638  -0.0118   0.7849   0.0704
  -4.500  -0.3582   0.01428   0.00600  -0.0109   0.7654   0.0792
  -4.000  -0.3100   0.01371   0.00531  -0.0093   0.7301   0.1007
  -3.750  -0.2855   0.01345   0.00500  -0.0086   0.7138   0.1140
  -3.500  -0.2609   0.01320   0.00471  -0.0080   0.6981   0.1302
  -3.250  -0.2362   0.01295   0.00443  -0.0073   0.6836   0.1498
  -3.000  -0.2118   0.01267   0.00418  -0.0066   0.6696   0.1769
  -2.750  -0.1878   0.01237   0.00393  -0.0059   0.6563   0.2130
  -2.500  -0.1645   0.01196   0.00370  -0.0052   0.6435   0.2702
  -2.250  -0.1437   0.01136   0.00345  -0.0040   0.6311   0.3708
  -2.000  -0.1273   0.01053   0.00328  -0.0019   0.6198   0.5381
  -1.750  -0.1080   0.01008   0.00331   0.0002   0.6088   0.6738
  -1.500  -0.0836   0.00999   0.00336   0.0015   0.5976   0.7434
  -1.250  -0.0574   0.01001   0.00340   0.0024   0.5862   0.7852
  -1.000  -0.0306   0.01007   0.00343   0.0031   0.5754   0.8149
  -0.750  -0.0038   0.01016   0.00346   0.0037   0.5651   0.8391
  -0.500   0.0231   0.01029   0.00353   0.0045   0.5547   0.8645
  -0.250   0.0528   0.01046   0.00366   0.0048   0.5444   0.8866
   0.000   0.0830   0.01068   0.00380   0.0049   0.5347   0.9071
   0.250   0.1169   0.01090   0.00393   0.0043   0.5244   0.9216
   0.500   0.1488   0.01100   0.00395   0.0036   0.5145   0.9288
   0.750   0.1815   0.01109   0.00393   0.0027   0.5051   0.9331
   1.000   0.2102   0.01115   0.00392   0.0025   0.4957   0.9393
   1.250   0.2429   0.01123   0.00393   0.0015   0.4865   0.9432
   1.500   0.2769   0.01133   0.00394   0.0002   0.4775   0.9466
   1.750   0.3091   0.01140   0.00396  -0.0007   0.4678   0.9511
   2.000   0.3385   0.01149   0.00399  -0.0011   0.4594   0.9564
   2.250   0.3741   0.01158   0.00403  -0.0028   0.4502   0.9589
   2.500   0.4080   0.01166   0.00408  -0.0042   0.4412   0.9622
   2.750   0.4392   0.01177   0.00412  -0.0050   0.4330   0.9667
   3.000   0.4703   0.01186   0.00421  -0.0058   0.4241   0.9709
   3.250   0.5048   0.01196   0.00428  -0.0073   0.4157   0.9738
   3.500   0.5376   0.01206   0.00436  -0.0085   0.4070   0.9774
   3.750   0.5683   0.01218   0.00448  -0.0093   0.3985   0.9818
   4.000   0.6014   0.01230   0.00457  -0.0106   0.3902   0.9849
   4.250   0.6349   0.01240   0.00470  -0.0120   0.3814   0.9881
   4.500   0.6670   0.01255   0.00484  -0.0131   0.3733   0.9918
   4.750   0.6995   0.01268   0.00500  -0.0143   0.3645   0.9951
   5.000   0.7325   0.01282   0.00515  -0.0157   0.3561   0.9984
   5.250   0.7598   0.01299   0.00534  -0.0159   0.3479   1.0000
   5.500   0.7811   0.01316   0.00555  -0.0148   0.3407   1.0000
   5.750   0.8020   0.01335   0.00575  -0.0137   0.3333   1.0000
   6.000   0.8230   0.01354   0.00599  -0.0125   0.3256   1.0000
   6.250   0.8435   0.01377   0.00624  -0.0113   0.3179   1.0000
   6.500   0.8644   0.01398   0.00651  -0.0102   0.3099   1.0000
   6.750   0.8846   0.01424   0.00677  -0.0089   0.3023   1.0000
   7.000   0.9056   0.01447   0.00708  -0.0078   0.2938   1.0000
   7.250   0.9258   0.01476   0.00740  -0.0065   0.2862   1.0000
   7.500   0.9463   0.01503   0.00774  -0.0053   0.2772   1.0000
   7.750   0.9667   0.01533   0.00809  -0.0041   0.2688   1.0000
   8.000   0.9864   0.01567   0.00845  -0.0029   0.2596   1.0000
   8.250   1.0068   0.01598   0.00884  -0.0017   0.2496   1.0000
   8.500   1.0263   0.01634   0.00927  -0.0005   0.2384   1.0000
   8.750   1.0445   0.01675   0.00968   0.0009   0.2220   1.0000
   9.000   1.0610   0.01729   0.01014   0.0024   0.1996   1.0000
   9.250   1.0767   0.01792   0.01070   0.0040   0.1763   1.0000
   9.500   1.0923   0.01859   0.01133   0.0055   0.1560   1.0000
   9.750   1.1064   0.01936   0.01206   0.0071   0.1361   1.0000
  10.000   1.1184   0.02027   0.01290   0.0090   0.1137   1.0000
  10.250   1.1275   0.02134   0.01387   0.0111   0.0921   1.0000
  10.500   1.1325   0.02261   0.01503   0.0135   0.0698   1.0000
  10.750   1.1322   0.02398   0.01630   0.0167   0.0512   1.0000
  11.000   1.1286   0.02547   0.01774   0.0199   0.0388   1.0000
  11.500   1.1267   0.02883   0.02118   0.0239   0.0273   1.0000
  11.750   1.1238   0.03102   0.02343   0.0250   0.0242   1.0000
  12.000   1.1230   0.03328   0.02580   0.0256   0.0223   1.0000
  12.250   1.1217   0.03579   0.02843   0.0257   0.0208   1.0000
  12.500   1.1184   0.03866   0.03142   0.0256   0.0195   1.0000
  12.750   1.1131   0.04192   0.03478   0.0251   0.0186   1.0000
  13.250   1.1025   0.04882   0.04192   0.0235   0.0170   1.0000
  13.500   1.0976   0.05238   0.04561   0.0225   0.0165   1.0000
  13.750   1.0912   0.05621   0.04956   0.0214   0.0157   1.0000
  14.000   1.0849   0.06011   0.05357   0.0201   0.0154   1.0000
  14.250   1.0773   0.06428   0.05785   0.0187   0.0149   1.0000
  14.500   1.0701   0.06856   0.06223   0.0171   0.0146   1.0000
  14.750   1.0623   0.07307   0.06684   0.0153   0.0143   1.0000
  15.000   1.0543   0.07772   0.07158   0.0135   0.0140   1.0000
  15.250   1.0473   0.08230   0.07625   0.0116   0.0138   1.0000
  15.500   1.0395   0.08707   0.08109   0.0097   0.0135   1.0000
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