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E186 (10.27%) (e186-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: E186 (10.27%) (e186-il)
Reynolds number: 100,000
Max Cl/Cd: 46.03 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e186-il-100000.txt
Download as CSV file: xf-e186-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E186  (10.27%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.6224   0.11676   0.11247   0.0311   1.0000   0.1056
  -9.750  -0.6434   0.11269   0.10852   0.0240   1.0000   0.1096
  -9.500  -0.6732   0.10790   0.10386   0.0146   1.0000   0.1103
  -9.250  -0.6230   0.10370   0.09956   0.0245   1.0000   0.1153
  -9.000  -0.6238   0.09969   0.09559   0.0222   1.0000   0.1203
  -8.750  -0.6597   0.09428   0.09031   0.0119   1.0000   0.1236
  -8.500  -0.6591   0.08899   0.08507   0.0109   1.0000   0.1260
  -8.250  -0.6353   0.08627   0.08235   0.0141   1.0000   0.1327
  -8.000  -0.6634   0.08148   0.07758   0.0087   1.0000   0.1367
  -7.750  -0.5701   0.06990   0.06640   0.0062   1.0000   0.1555
  -7.500  -0.6663   0.07330   0.06934   0.0064   1.0000   0.1508
  -7.250  -0.6528   0.06943   0.06554   0.0074   1.0000   0.1589
  -6.500  -0.6564   0.04479   0.03895   0.0032   1.0000   0.0814
  -6.250  -0.6414   0.03871   0.03214   0.0050   1.0000   0.0680
  -6.000  -0.6212   0.03457   0.02768   0.0055   1.0000   0.0647
  -5.750  -0.5984   0.03088   0.02344   0.0061   1.0000   0.0619
  -5.500  -0.5729   0.02798   0.02003   0.0062   1.0000   0.0607
  -5.250  -0.5488   0.02592   0.01768   0.0059   0.9929   0.0612
  -5.000  -0.4996   0.02388   0.01531   0.0017   0.9681   0.0668
  -4.750  -0.4547   0.02206   0.01317  -0.0010   0.9468   0.0698
  -4.500  -0.4222   0.02023   0.01143  -0.0017   0.9257   0.0754
  -4.250  -0.3989   0.01925   0.01037  -0.0003   0.9052   0.0839
  -4.000  -0.3815   0.01825   0.00948   0.0021   0.8879   0.1051
  -3.750  -0.3714   0.01612   0.00837   0.0055   0.8730   0.2527
  -3.500  -0.3596   0.01485   0.00807   0.0086   0.8591   0.4505
  -3.250  -0.3007   0.01382   0.00860   0.0059   0.8489   0.8257
  -3.000  -0.2357   0.01485   0.00928   0.0019   0.8383   0.9059
  -2.750  -0.1774   0.01570   0.00974  -0.0022   0.8276   0.9452
  -2.500  -0.1085   0.01602   0.00965  -0.0094   0.8165   0.9758
  -2.250  -0.0396   0.01567   0.00898  -0.0178   0.8047   1.0000
  -2.000  -0.0205   0.01555   0.00868  -0.0171   0.7936   1.0000
  -1.750  -0.0012   0.01549   0.00843  -0.0162   0.7835   1.0000
  -1.500   0.0187   0.01546   0.00824  -0.0152   0.7741   1.0000
  -1.250   0.0414   0.01548   0.00813  -0.0149   0.7640   1.0000
  -1.000   0.0629   0.01553   0.00804  -0.0141   0.7555   1.0000
  -0.750   0.0854   0.01559   0.00798  -0.0135   0.7467   1.0000
  -0.500   0.1092   0.01570   0.00800  -0.0132   0.7380   1.0000
  -0.250   0.1309   0.01580   0.00798  -0.0122   0.7306   1.0000
   0.000   0.1563   0.01597   0.00810  -0.0123   0.7216   1.0000
   0.250   0.1784   0.01611   0.00813  -0.0113   0.7148   1.0000
   0.500   0.2042   0.01631   0.00831  -0.0114   0.7060   1.0000
   0.750   0.2276   0.01650   0.00844  -0.0107   0.6990   1.0000
   1.000   0.2527   0.01672   0.00866  -0.0106   0.6908   1.0000
   1.250   0.2768   0.01697   0.00888  -0.0101   0.6837   1.0000
   1.500   0.3013   0.01722   0.00913  -0.0098   0.6759   1.0000
   1.750   0.3259   0.01753   0.00943  -0.0094   0.6686   1.0000
   2.000   0.3501   0.01779   0.00972  -0.0089   0.6610   1.0000
   2.250   0.3749   0.01814   0.01011  -0.0087   0.6531   1.0000
   2.500   0.3984   0.01839   0.01036  -0.0079   0.6458   1.0000
   2.750   0.4235   0.01880   0.01083  -0.0078   0.6371   1.0000
   3.000   0.4460   0.01898   0.01102  -0.0065   0.6302   1.0000
   3.250   0.4711   0.01939   0.01154  -0.0064   0.6201   1.0000
   3.500   0.4941   0.01962   0.01180  -0.0053   0.6121   1.0000
   3.750   0.5174   0.01983   0.01206  -0.0044   0.6027   1.0000
   4.000   0.5414   0.02016   0.01252  -0.0038   0.5920   1.0000
   4.250   0.5641   0.02027   0.01268  -0.0024   0.5826   1.0000
   4.500   0.5868   0.02027   0.01271  -0.0009   0.5726   1.0000
   4.750   0.6102   0.02038   0.01293   0.0001   0.5601   1.0000
   5.000   0.6333   0.02039   0.01304   0.0014   0.5475   1.0000
   5.250   0.6564   0.02029   0.01305   0.0029   0.5343   1.0000
   5.500   0.6795   0.02007   0.01292   0.0045   0.5202   1.0000
   5.750   0.7027   0.01975   0.01268   0.0061   0.5049   1.0000
   6.000   0.7261   0.01930   0.01229   0.0079   0.4881   1.0000
   6.250   0.7495   0.01886   0.01197   0.0095   0.4679   1.0000
   6.500   0.7730   0.01832   0.01150   0.0113   0.4435   1.0000
   6.750   0.7962   0.01795   0.01130   0.0126   0.4085   1.0000
   7.000   0.8185   0.01778   0.01115   0.0139   0.3539   1.0000
   7.250   0.8345   0.01885   0.01161   0.0149   0.2419   1.0000
   7.500   0.8434   0.02143   0.01344   0.0157   0.1455   1.0000
   7.750   0.8493   0.02423   0.01575   0.0174   0.0887   1.0000
   8.000   0.8566   0.02658   0.01788   0.0196   0.0661   1.0000
   8.250   0.8674   0.02874   0.01984   0.0219   0.0569   1.0000
   8.500   0.8844   0.03038   0.02163   0.0237   0.0509   1.0000
   8.750   0.9006   0.03283   0.02392   0.0251   0.0457   1.0000
   9.000   0.9185   0.03466   0.02602   0.0267   0.0432   1.0000
   9.250   0.9368   0.03711   0.02872   0.0282   0.0419   1.0000
   9.500   0.9519   0.03992   0.03188   0.0297   0.0410   1.0000
   9.750   0.9625   0.04301   0.03533   0.0313   0.0407   1.0000
  10.000   0.9679   0.04632   0.03902   0.0331   0.0409   1.0000
  10.250   0.9674   0.04988   0.04296   0.0349   0.0412   1.0000
  10.500   0.9623   0.05343   0.04684   0.0366   0.0417   1.0000
  10.750   0.9511   0.05702   0.05069   0.0384   0.0422   1.0000
  11.000   0.9349   0.06021   0.05407   0.0401   0.0427   1.0000
  11.250   0.9170   0.06399   0.05803   0.0405   0.0431   1.0000
  11.500   0.8992   0.06821   0.06241   0.0398   0.0435   1.0000
  11.750   0.8802   0.07305   0.06739   0.0382   0.0439   1.0000
  12.000   0.8612   0.07841   0.07288   0.0359   0.0444   1.0000
  12.250   0.8433   0.08421   0.07876   0.0332   0.0449   1.0000
  12.500   0.7263   0.08215   0.07702   0.0351   0.0449   1.0000
  12.750   0.7058   0.08912   0.08401   0.0325   0.0454   1.0000
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