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E168 (12.45%) (e168-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: E168 (12.45%) (e168-il)
Reynolds number: 50,000
Max Cl/Cd: 22.61 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e168-il-50000.txt
Download as CSV file: xf-e168-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E168  (12.45%)                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.8344   0.07618   0.06930  -0.0201   1.0000   0.1375
 -10.750  -0.8628   0.06955   0.06263  -0.0227   1.0000   0.1363
 -10.500  -0.8927   0.06409   0.05705  -0.0229   1.0000   0.1353
 -10.250  -0.9179   0.05880   0.05152  -0.0225   1.0000   0.1352
 -10.000  -0.9382   0.05376   0.04604  -0.0214   1.0000   0.1367
  -9.750  -0.9254   0.05102   0.04330  -0.0202   1.0000   0.1445
  -9.500  -0.9332   0.04691   0.03866  -0.0185   1.0000   0.1508
  -9.250  -0.9199   0.04468   0.03641  -0.0171   1.0000   0.1636
  -9.000  -0.9091   0.04241   0.03401  -0.0155   1.0000   0.1784
  -8.750  -0.8958   0.04051   0.03207  -0.0138   1.0000   0.1962
  -8.500  -0.8758   0.03975   0.03147  -0.0120   1.0000   0.2190
  -8.250  -0.8585   0.03880   0.03057  -0.0101   1.0000   0.2430
  -8.000  -0.8459   0.03739   0.02894  -0.0081   1.0000   0.2677
  -7.750  -0.8199   0.03757   0.02936  -0.0061   1.0000   0.2938
  -7.500  -0.7976   0.03730   0.02915  -0.0041   1.0000   0.3183
  -7.250  -0.7830   0.03613   0.02778  -0.0023   1.0000   0.3424
  -7.000  -0.7543   0.03658   0.02837  -0.0001   1.0000   0.3642
  -6.750  -0.7369   0.03560   0.02725   0.0016   1.0000   0.3858
  -6.500  -0.7149   0.03511   0.02673   0.0035   1.0000   0.4057
  -6.250  -0.6915   0.03477   0.02638   0.0053   1.0000   0.4244
  -6.000  -0.6713   0.03399   0.02552   0.0070   1.0000   0.4429
  -5.750  -0.6529   0.03296   0.02435   0.0085   1.0000   0.4614
  -5.500  -0.6351   0.03185   0.02310   0.0099   1.0000   0.4794
  -5.250  -0.6132   0.03122   0.02246   0.0116   1.0000   0.4959
  -5.000  -0.5921   0.03050   0.02170   0.0132   1.0000   0.5122
  -4.750  -0.5715   0.02977   0.02092   0.0148   1.0000   0.5285
  -4.500  -0.5514   0.02900   0.02012   0.0164   1.0000   0.5448
  -4.250  -0.5317   0.02826   0.01935   0.0180   1.0000   0.5613
  -4.000  -0.5124   0.02752   0.01859   0.0197   1.0000   0.5779
  -3.750  -0.4936   0.02680   0.01785   0.0214   1.0000   0.5948
  -3.500  -0.4754   0.02609   0.01712   0.0231   1.0000   0.6120
  -3.250  -0.4582   0.02539   0.01642   0.0248   1.0000   0.6300
  -3.000  -0.4424   0.02468   0.01569   0.0266   1.0000   0.6485
  -2.750  -0.4263   0.02418   0.01525   0.0288   1.0000   0.6658
  -2.500  -0.4119   0.02371   0.01483   0.0311   1.0000   0.6834
  -2.250  -0.3995   0.02328   0.01445   0.0335   1.0000   0.7022
  -2.000  -0.3889   0.02286   0.01406   0.0358   1.0000   0.7222
  -1.750  -0.3783   0.02252   0.01373   0.0380   1.0000   0.7429
  -1.500  -0.3664   0.02231   0.01358   0.0401   1.0000   0.7642
  -1.250  -0.3564   0.02210   0.01340   0.0420   1.0000   0.7885
  -1.000  -0.3448   0.02200   0.01336   0.0439   1.0000   0.8137
  -0.750  -0.3308   0.02195   0.01337   0.0453   1.0000   0.8424
  -0.500  -0.2581   0.02271   0.01415   0.0365   0.9791   0.8787
  -0.250  -0.1466   0.02369   0.01511   0.0213   0.9567   0.9106
   0.000   0.0001   0.02421   0.01560   0.0000   0.9338   0.9338
   0.250   0.1461   0.02369   0.01511  -0.0213   0.9106   0.9566
   0.500   0.2578   0.02271   0.01416  -0.0365   0.8785   0.9789
   0.750   0.3308   0.02195   0.01337  -0.0453   0.8422   1.0000
   1.000   0.3448   0.02200   0.01336  -0.0439   0.8137   1.0000
   1.250   0.3564   0.02210   0.01340  -0.0420   0.7886   1.0000
   1.500   0.3663   0.02231   0.01358  -0.0401   0.7643   1.0000
   1.750   0.3783   0.02251   0.01373  -0.0380   0.7429   1.0000
   2.000   0.3888   0.02286   0.01406  -0.0358   0.7221   1.0000
   2.250   0.3995   0.02328   0.01445  -0.0335   0.7021   1.0000
   2.500   0.4119   0.02371   0.01483  -0.0310   0.6834   1.0000
   2.750   0.4263   0.02418   0.01525  -0.0288   0.6657   1.0000
   3.000   0.4424   0.02467   0.01570  -0.0266   0.6485   1.0000
   3.250   0.4582   0.02539   0.01642  -0.0248   0.6300   1.0000
   3.500   0.4754   0.02609   0.01713  -0.0231   0.6121   1.0000
   3.750   0.4936   0.02680   0.01784  -0.0214   0.5948   1.0000
   4.000   0.5124   0.02752   0.01857  -0.0197   0.5779   1.0000
   4.250   0.5317   0.02826   0.01935  -0.0180   0.5613   1.0000
   4.500   0.5514   0.02900   0.02011  -0.0164   0.5448   1.0000
   4.750   0.5716   0.02976   0.02091  -0.0148   0.5285   1.0000
   5.000   0.5921   0.03049   0.02169  -0.0132   0.5122   1.0000
   5.250   0.6132   0.03122   0.02245  -0.0116   0.4959   1.0000
   5.500   0.6350   0.03185   0.02311  -0.0099   0.4794   1.0000
   5.750   0.6529   0.03297   0.02436  -0.0085   0.4614   1.0000
   6.250   0.6915   0.03476   0.02637  -0.0053   0.4244   1.0000
   6.500   0.7149   0.03512   0.02674  -0.0035   0.4057   1.0000
   6.750   0.7368   0.03560   0.02725  -0.0016   0.3858   1.0000
   7.000   0.7543   0.03658   0.02837   0.0001   0.3642   1.0000
   7.250   0.7830   0.03613   0.02778   0.0023   0.3423   1.0000
   7.500   0.7976   0.03729   0.02914   0.0041   0.3183   1.0000
   7.750   0.8198   0.03756   0.02936   0.0061   0.2938   1.0000
   8.000   0.8457   0.03740   0.02895   0.0081   0.2676   1.0000
   8.250   0.8585   0.03880   0.03057   0.0101   0.2429   1.0000
   8.500   0.8758   0.03975   0.03148   0.0120   0.2190   1.0000
   8.750   0.8960   0.04048   0.03202   0.0138   0.1961   1.0000
   9.000   0.9089   0.04243   0.03403   0.0155   0.1783   1.0000
   9.250   0.9197   0.04469   0.03642   0.0171   0.1635   1.0000
   9.500   0.9333   0.04692   0.03865   0.0185   0.1509   1.0000
   9.750   0.9253   0.05105   0.04333   0.0202   0.1447   1.0000
  10.000   0.9384   0.05375   0.04603   0.0213   0.1367   1.0000
  10.250   0.9182   0.05878   0.05150   0.0225   0.1352   1.0000
  10.500   0.8926   0.06413   0.05709   0.0229   0.1353   1.0000
  10.750   0.8631   0.06958   0.06265   0.0226   0.1363   1.0000
  11.000   0.8351   0.07617   0.06929   0.0201   0.1375   1.0000
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