Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EH 1.0/9.0 (eh1090-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: EH 1.0/9.0 (eh1090-il)
Reynolds number: 500,000
Max Cl/Cd: 68.85 at α=4.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-eh1090-il-500000-n5.txt
Download as CSV file: xf-eh1090-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EH 1.0/9.0                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.8159   0.04508   0.04257  -0.0214   1.0000   0.0049
  -9.500  -0.8345   0.03911   0.03619  -0.0197   1.0000   0.0049
  -9.250  -0.8395   0.03452   0.03117  -0.0179   1.0000   0.0050
  -9.000  -0.8339   0.03119   0.02745  -0.0162   1.0000   0.0051
  -8.750  -0.8236   0.02841   0.02429  -0.0147   1.0000   0.0052
  -8.500  -0.8163   0.02471   0.02010  -0.0127   1.0000   0.0054
  -8.250  -0.8003   0.02261   0.01771  -0.0114   1.0000   0.0056
  -8.000  -0.7808   0.02125   0.01613  -0.0105   1.0000   0.0058
  -7.750  -0.7602   0.02001   0.01471  -0.0096   1.0000   0.0060
  -7.500  -0.7381   0.01913   0.01372  -0.0088   1.0000   0.0063
  -7.250  -0.7155   0.01835   0.01283  -0.0082   1.0000   0.0067
  -7.000  -0.6929   0.01747   0.01182  -0.0074   1.0000   0.0071
  -6.750  -0.6707   0.01650   0.01070  -0.0064   1.0000   0.0074
  -6.500  -0.6488   0.01547   0.00952  -0.0054   1.0000   0.0076
  -6.250  -0.6266   0.01460   0.00854  -0.0044   1.0000   0.0078
  -6.000  -0.6043   0.01386   0.00767  -0.0033   1.0000   0.0082
  -5.750  -0.5819   0.01325   0.00697  -0.0023   1.0000   0.0085
  -5.500  -0.5604   0.01251   0.00615  -0.0011   0.9999   0.0089
  -5.250  -0.5277   0.01177   0.00533  -0.0023   0.9915   0.0100
  -5.000  -0.4940   0.01130   0.00481  -0.0038   0.9817   0.0111
  -4.750  -0.4606   0.01089   0.00435  -0.0050   0.9686   0.0126
  -4.500  -0.4277   0.01049   0.00387  -0.0061   0.9517   0.0157
  -4.250  -0.3961   0.01012   0.00349  -0.0069   0.9303   0.0220
  -4.000  -0.3687   0.00981   0.00316  -0.0067   0.9052   0.0336
  -3.750  -0.3436   0.00957   0.00290  -0.0060   0.8790   0.0470
  -3.500  -0.3189   0.00934   0.00266  -0.0053   0.8534   0.0667
  -3.250  -0.2943   0.00910   0.00243  -0.0046   0.8285   0.0951
  -3.000  -0.2693   0.00886   0.00223  -0.0040   0.8044   0.1261
  -2.750  -0.2440   0.00864   0.00204  -0.0035   0.7812   0.1614
  -2.500  -0.2188   0.00839   0.00186  -0.0030   0.7590   0.2069
  -2.250  -0.1937   0.00810   0.00170  -0.0025   0.7373   0.2660
  -2.000  -0.1685   0.00781   0.00153  -0.0021   0.7169   0.3310
  -1.750  -0.1438   0.00748   0.00139  -0.0016   0.6967   0.4115
  -1.500  -0.1205   0.00700   0.00127  -0.0009   0.6777   0.5288
  -1.250  -0.0961   0.00672   0.00120  -0.0002   0.6591   0.6097
  -1.000  -0.0710   0.00654   0.00115   0.0005   0.6410   0.6701
  -0.750  -0.0452   0.00647   0.00112   0.0010   0.6234   0.7103
  -0.500  -0.0195   0.00639   0.00111   0.0016   0.6063   0.7520
  -0.250   0.0059   0.00634   0.00112   0.0023   0.5896   0.7937
   0.000   0.0317   0.00633   0.00114   0.0030   0.5729   0.8265
   0.250   0.0578   0.00635   0.00116   0.0035   0.5565   0.8518
   0.500   0.0838   0.00638   0.00120   0.0042   0.5408   0.8758
   0.750   0.1099   0.00644   0.00124   0.0048   0.5257   0.8980
   1.000   0.1367   0.00651   0.00129   0.0052   0.5107   0.9154
   1.250   0.1644   0.00660   0.00134   0.0054   0.4959   0.9289
   1.500   0.1931   0.00670   0.00139   0.0054   0.4804   0.9393
   1.750   0.2232   0.00680   0.00144   0.0049   0.4645   0.9465
   2.000   0.2525   0.00690   0.00150   0.0047   0.4491   0.9543
   2.250   0.2846   0.00702   0.00156   0.0038   0.4331   0.9597
   2.500   0.3154   0.00714   0.00163   0.0031   0.4174   0.9662
   2.750   0.3471   0.00727   0.00173   0.0023   0.4014   0.9712
   3.000   0.3799   0.00742   0.00182   0.0011   0.3823   0.9751
   3.250   0.4112   0.00760   0.00191   0.0003   0.3590   0.9797
   3.500   0.4433   0.00775   0.00203  -0.0008   0.3407   0.9834
   3.750   0.4773   0.00790   0.00216  -0.0022   0.3245   0.9860
   4.000   0.5103   0.00806   0.00230  -0.0035   0.3089   0.9893
   4.250   0.5421   0.00828   0.00246  -0.0045   0.2870   0.9927
   4.500   0.5743   0.00851   0.00263  -0.0056   0.2626   0.9956
   4.750   0.6066   0.00881   0.00285  -0.0069   0.2314   0.9984
   5.000   0.6326   0.00945   0.00315  -0.0071   0.1639   1.0000
   5.250   0.6530   0.01003   0.00349  -0.0060   0.1145   1.0000
   5.500   0.6744   0.01051   0.00384  -0.0050   0.0839   1.0000
   5.750   0.6955   0.01106   0.00424  -0.0040   0.0527   1.0000
   6.000   0.7165   0.01165   0.00471  -0.0029   0.0277   1.0000
   6.250   0.7384   0.01213   0.00519  -0.0020   0.0173   1.0000
   6.500   0.7605   0.01262   0.00569  -0.0010   0.0131   1.0000
   6.750   0.7829   0.01308   0.00621  -0.0001   0.0108   1.0000
   7.000   0.8055   0.01353   0.00674   0.0008   0.0099   1.0000
   7.250   0.8279   0.01404   0.00732   0.0016   0.0091   1.0000
   7.500   0.8499   0.01463   0.00798   0.0025   0.0083   1.0000
   7.750   0.8701   0.01548   0.00895   0.0035   0.0074   1.0000
   8.000   0.8909   0.01623   0.00980   0.0045   0.0068   1.0000
   8.250   0.9134   0.01674   0.01038   0.0052   0.0062   1.0000
   8.500   0.9340   0.01749   0.01122   0.0061   0.0058   1.0000
   8.750   0.9540   0.01831   0.01214   0.0070   0.0054   1.0000
   9.000   0.9738   0.01912   0.01303   0.0080   0.0051   1.0000
   9.250   0.9925   0.02003   0.01403   0.0090   0.0048   1.0000
   9.500   1.0098   0.02107   0.01517   0.0101   0.0046   1.0000
   9.750   1.0221   0.02267   0.01692   0.0118   0.0043   1.0000
  10.000   1.0338   0.02430   0.01875   0.0135   0.0041   1.0000
  10.250   1.0475   0.02560   0.02020   0.0149   0.0040   1.0000
  10.500   1.0591   0.02702   0.02180   0.0164   0.0039   1.0000
  10.750   1.0679   0.02862   0.02358   0.0182   0.0037   1.0000
  11.000   1.0708   0.03036   0.02551   0.0207   0.0037   1.0000
  11.250   1.0693   0.03226   0.02759   0.0233   0.0037   1.0000
  11.500   1.0649   0.03458   0.03011   0.0253   0.0036   1.0000
  11.750   1.0609   0.03705   0.03277   0.0263   0.0035   1.0000
  12.000   1.0542   0.04015   0.03606   0.0265   0.0035   1.0000
  12.250   1.0439   0.04406   0.04018   0.0257   0.0034   1.0000
  12.500   1.0339   0.04835   0.04466   0.0240   0.0034   1.0000
  12.750   1.0238   0.05303   0.04950   0.0216   0.0035   1.0000
  13.000   1.0060   0.05938   0.05607   0.0180   0.0034   1.0000
  13.250   0.9943   0.06508   0.06192   0.0145   0.0035   1.0000
  13.500   0.9775   0.07208   0.06907   0.0101   0.0035   1.0000
  13.750   0.9585   0.07993   0.07708   0.0052   0.0034   1.0000
  14.000   0.9411   0.08783   0.08510   0.0003   0.0035   1.0000
  14.250   0.9220   0.09660   0.09399  -0.0050   0.0036   1.0000
  14.500   0.9009   0.10651   0.10402  -0.0108   0.0035   1.0000
  14.750   0.8793   0.11710   0.11471  -0.0166   0.0037   1.0000
  15.000   0.8479   0.13126   0.12897  -0.0239   0.0038   1.0000
<< Back to EH 1.0/9.0 (eh1090-il)

Polar data table (+)

Polar graphs


<< Back to EH 1.0/9.0 (eh1090-il)