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EH 2.0/7.0 (eh2070-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EH 2.0/7.0 (eh2070-il)
Reynolds number: 200,000
Max Cl/Cd: 58.63 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh2070-il-200000-n5.txt
Download as CSV file: xf-eh2070-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 2.0/7.0                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.5343   0.09732   0.09405   0.0073   1.0000   0.0186
  -8.000  -0.5333   0.09332   0.09008   0.0046   1.0000   0.0187
  -7.750  -0.5334   0.08943   0.08623   0.0017   1.0000   0.0187
  -7.500  -0.5299   0.08531   0.08210  -0.0010   1.0000   0.0187
  -7.250  -0.5242   0.08105   0.07782  -0.0035   1.0000   0.0187
  -7.000  -0.5170   0.07676   0.07349  -0.0058   1.0000   0.0187
  -6.750  -0.5083   0.07241   0.06909  -0.0077   1.0000   0.0187
  -6.500  -0.4982   0.06799   0.06458  -0.0092   1.0000   0.0187
  -6.250  -0.4866   0.06371   0.06021  -0.0105   1.0000   0.0187
  -5.750  -0.4761   0.05330   0.04969  -0.0117   1.0000   0.0155
  -5.500  -0.4607   0.04858   0.04480  -0.0124   1.0000   0.0140
  -5.250  -0.4430   0.04355   0.03951  -0.0127   1.0000   0.0127
  -5.000  -0.4236   0.03759   0.03318  -0.0122   1.0000   0.0114
  -4.750  -0.4030   0.03228   0.02744  -0.0111   1.0000   0.0108
  -4.500  -0.3823   0.02819   0.02294  -0.0099   1.0000   0.0107
  -4.250  -0.3608   0.02491   0.01924  -0.0088   1.0000   0.0110
  -4.000  -0.3381   0.02270   0.01670  -0.0079   1.0000   0.0119
  -3.750  -0.3143   0.02171   0.01554  -0.0074   1.0000   0.0146
  -3.500  -0.2823   0.01921   0.01258  -0.0078   0.9774   0.0153
  -3.250  -0.2449   0.01693   0.00985  -0.0092   0.9387   0.0152
  -3.000  -0.2097   0.01528   0.00781  -0.0102   0.8971   0.0152
  -2.750  -0.1815   0.01413   0.00640  -0.0096   0.8561   0.0156
  -2.500  -0.1568   0.01329   0.00533  -0.0085   0.8197   0.0162
  -2.250  -0.1328   0.01267   0.00449  -0.0073   0.7882   0.0173
  -2.000  -0.1084   0.01215   0.00374  -0.0063   0.7610   0.0197
  -1.750  -0.0837   0.01170   0.00315  -0.0053   0.7365   0.0311
  -1.500  -0.0597   0.01120   0.00287  -0.0047   0.7145   0.0954
  -1.250  -0.0359   0.01066   0.00257  -0.0041   0.6941   0.1979
  -1.000  -0.0282   0.00847   0.00247   0.0000   0.6776   0.7734
  -0.750   0.0055   0.00844   0.00255   0.0002   0.6595   0.9145
  -0.500   0.0515   0.00860   0.00249  -0.0029   0.6404   0.9579
  -0.250   0.1008   0.00873   0.00239  -0.0072   0.6215   0.9793
   0.000   0.1654   0.00879   0.00219  -0.0149   0.6019   0.9995
   0.250   0.1901   0.00883   0.00208  -0.0144   0.5870   1.0000
   0.500   0.2138   0.00887   0.00200  -0.0137   0.5728   1.0000
   0.750   0.2375   0.00893   0.00195  -0.0129   0.5593   1.0000
   1.000   0.2614   0.00900   0.00192  -0.0122   0.5459   1.0000
   1.250   0.2854   0.00907   0.00191  -0.0115   0.5330   1.0000
   1.500   0.3095   0.00915   0.00191  -0.0109   0.5204   1.0000
   1.750   0.3336   0.00925   0.00193  -0.0102   0.5084   1.0000
   2.000   0.3579   0.00935   0.00198  -0.0095   0.4965   1.0000
   2.250   0.3823   0.00947   0.00207  -0.0089   0.4849   1.0000
   2.500   0.4067   0.00958   0.00215  -0.0083   0.4730   1.0000
   2.750   0.4313   0.00971   0.00225  -0.0077   0.4609   1.0000
   3.000   0.4560   0.00984   0.00237  -0.0071   0.4488   1.0000
   3.250   0.4807   0.00998   0.00251  -0.0065   0.4371   1.0000
   3.500   0.5055   0.01013   0.00267  -0.0060   0.4258   1.0000
   3.750   0.5303   0.01030   0.00291  -0.0055   0.4148   1.0000
   4.000   0.5552   0.01048   0.00311  -0.0049   0.4044   1.0000
   4.250   0.5802   0.01066   0.00334  -0.0044   0.3929   1.0000
   4.500   0.6051   0.01085   0.00358  -0.0039   0.3799   1.0000
   4.750   0.6301   0.01105   0.00385  -0.0034   0.3663   1.0000
   5.000   0.6551   0.01128   0.00414  -0.0029   0.3521   1.0000
   5.250   0.6789   0.01158   0.00443  -0.0023   0.3041   1.0000
   5.500   0.6993   0.01251   0.00479  -0.0016   0.1909   1.0000
   5.750   0.7142   0.01478   0.00608  -0.0008   0.0276   1.0000
   6.000   0.7364   0.01582   0.00725   0.0002   0.0169   1.0000
   6.250   0.7595   0.01653   0.00812   0.0008   0.0125   1.0000
   6.500   0.7803   0.01770   0.00949   0.0017   0.0101   1.0000
   6.750   0.7973   0.01950   0.01151   0.0030   0.0091   1.0000
   7.000   0.8151   0.02111   0.01324   0.0042   0.0087   1.0000
   7.250   0.8341   0.02264   0.01490   0.0054   0.0084   1.0000
   7.500   0.8530   0.02437   0.01678   0.0066   0.0083   1.0000
   7.750   0.8721   0.02630   0.01897   0.0077   0.0081   1.0000
   8.000   0.8908   0.02851   0.02141   0.0089   0.0079   1.0000
   8.250   0.9101   0.03003   0.02318   0.0098   0.0069   1.0000
   8.500   0.9276   0.03159   0.02497   0.0106   0.0060   1.0000
   8.750   0.9431   0.03328   0.02687   0.0114   0.0053   1.0000
   9.000   0.9550   0.03566   0.02953   0.0124   0.0050   1.0000
   9.250   0.9635   0.03841   0.03259   0.0136   0.0048   1.0000
   9.500   0.9677   0.04143   0.03591   0.0148   0.0047   1.0000
   9.750   0.9671   0.04454   0.03930   0.0160   0.0046   1.0000
  10.000   0.9593   0.04765   0.04266   0.0176   0.0045   1.0000
  10.250   0.9480   0.05081   0.04604   0.0184   0.0045   1.0000
  10.500   0.9360   0.05459   0.05002   0.0175   0.0045   1.0000
  10.750   0.9243   0.05895   0.05458   0.0153   0.0045   1.0000
  11.000   0.9094   0.06434   0.06013   0.0119   0.0045   1.0000
  11.250   0.8976   0.07017   0.06617   0.0080   0.0047   1.0000
  11.500   0.8829   0.07667   0.07279   0.0033   0.0046   1.0000
  11.750   0.8679   0.08402   0.08028  -0.0018   0.0047   1.0000
  12.000   0.8511   0.09259   0.08897  -0.0076   0.0048   1.0000
  12.250   0.8302   0.10356   0.10006  -0.0143   0.0051   1.0000
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