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EPPLER 378 AIRFOIL (e378-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 378 AIRFOIL (e378-il)
Reynolds number: 50,000
Max Cl/Cd: 32.59 at α=10.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e378-il-50000.txt
Download as CSV file: xf-e378-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 378 AIRFOIL                              
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2475   0.11394   0.10783  -0.0183   1.0000   0.0616
  -7.750  -0.2441   0.11183   0.10580  -0.0181   1.0000   0.0630
  -7.500  -0.2566   0.11189   0.10599  -0.0157   1.0000   0.0635
  -7.250  -0.2462   0.10887   0.10301  -0.0161   1.0000   0.0654
  -7.000  -0.2308   0.10579   0.09997  -0.0174   1.0000   0.0675
  -6.750  -0.2432   0.10603   0.10032  -0.0154   1.0000   0.0681
  -6.500  -0.2403   0.10541   0.09978  -0.0161   1.0000   0.0692
  -6.250  -0.2206   0.10540   0.09980  -0.0209   1.0000   0.0702
  -6.000  -0.2077   0.10663   0.10108  -0.0255   1.0000   0.0705
  -5.750  -0.2101   0.09861   0.09321  -0.0198   1.0000   0.0715
  -5.500  -0.2154   0.09579   0.09045  -0.0171   1.0000   0.0726
  -5.250  -0.2080   0.09261   0.08739  -0.0162   1.0000   0.0744
  -5.000  -0.2076   0.09079   0.08574  -0.0153   1.0000   0.0763
  -4.750  -0.2156   0.09028   0.08537  -0.0140   1.0000   0.0772
  -4.500  -0.2243   0.08997   0.08516  -0.0130   1.0000   0.0781
  -4.250  -0.2001   0.08825   0.08345  -0.0195   0.9930   0.0815
  -4.000  -0.1362   0.08747   0.08251  -0.0360   0.9830   0.0846
  -3.750  -0.0961   0.07928   0.07434  -0.0411   0.9630   0.0891
  -3.500  -0.0394   0.07669   0.07157  -0.0529   0.9503   0.0967
  -3.250   0.0069   0.07238   0.06721  -0.0613   0.9379   0.1006
  -3.000   0.0462   0.06943   0.06416  -0.0677   0.9293   0.1093
  -2.750   0.1017   0.06531   0.05996  -0.0769   0.9147   0.1170
  -2.500   0.1650   0.06273   0.05718  -0.0880   0.9011   0.1270
  -2.250   0.2246   0.06159   0.05582  -0.0976   0.8879   0.1391
  -2.000   0.2401   0.05705   0.05135  -0.0972   0.8781   0.1442
  -1.750   0.2846   0.05477   0.04891  -0.1031   0.8712   0.1559
  -1.500   0.3255   0.05250   0.04654  -0.1075   0.8572   0.1703
  -1.250   0.3521   0.05090   0.04482  -0.1096   0.8491   0.1867
  -1.000   0.3973   0.04877   0.04253  -0.1142   0.8395   0.2103
  -0.750   0.4221   0.04735   0.04101  -0.1154   0.8303   0.2288
  -0.500   0.4530   0.04586   0.03942  -0.1175   0.8200   0.2541
  -0.250   0.4887   0.04362   0.03706  -0.1196   0.8120   0.3074
   0.000   0.5058   0.04215   0.03556  -0.1193   0.8013   0.3634
   0.500   0.5552   0.03752   0.03082  -0.1195   0.7832   0.5267
   0.750   0.5752   0.03666   0.02989  -0.1196   0.7727   0.5698
   1.000   0.6171   0.03579   0.02871  -0.1224   0.7666   0.5792
   1.250   0.6577   0.03601   0.02833  -0.1242   0.7688   0.5258
   1.500   0.6840   0.03760   0.02947  -0.1232   0.7705   0.4221
   1.750   0.7215   0.03894   0.03023  -0.1228   0.7696   0.2867
   2.000   0.7278   0.03944   0.03054  -0.1183   0.7718   0.2864
   2.250   0.7427   0.04013   0.03099  -0.1164   0.7597   0.2749
   2.500   0.7608   0.04028   0.03098  -0.1137   0.7542   0.2728
   2.750   0.7267   0.04251   0.03334  -0.1035   0.7474   0.2705
   3.000   0.7361   0.04301   0.03378  -0.1012   0.7335   0.2855
   3.250   0.7774   0.04204   0.03260  -0.1019   0.7247   0.2916
   3.500   0.8095   0.04134   0.03182  -0.1009   0.7176   0.3138
   3.750   0.8921   0.03828   0.02853  -0.1073   0.7107   0.3491
   4.000   0.9345   0.03724   0.02748  -0.1080   0.7037   0.3898
   4.250   0.9980   0.03480   0.02539  -0.1117   0.6973   0.4896
   4.500   1.0428   0.03554   0.02601  -0.1161   0.6839   0.8380
   4.750   1.0647   0.03744   0.02849  -0.1179   0.6705   1.0000
   5.000   1.0820   0.04004   0.03094  -0.1185   0.6600   1.0000
   5.250   1.1165   0.04021   0.03096  -0.1181   0.6527   1.0000
   5.500   1.1175   0.04352   0.03434  -0.1169   0.6416   1.0000
   5.750   1.1235   0.04732   0.03813  -0.1173   0.6299   1.0000
   6.000   1.1532   0.04789   0.03880  -0.1165   0.6211   1.0000
   6.250   1.1615   0.05005   0.04106  -0.1146   0.6109   1.0000
   6.500   1.1563   0.05420   0.04528  -0.1136   0.5989   1.0000
   6.750   1.1647   0.05623   0.04743  -0.1112   0.5888   1.0000
   7.000   1.1748   0.05956   0.05079  -0.1116   0.5758   1.0000
   7.250   1.2271   0.05741   0.04879  -0.1097   0.5653   1.0000
   7.500   1.2181   0.06144   0.05302  -0.1079   0.5521   1.0000
   7.750   1.2186   0.06492   0.05659  -0.1068   0.5381   1.0000
   8.000   1.2406   0.06677   0.05853  -0.1068   0.5228   1.0000
   8.250   1.2304   0.07054   0.06243  -0.1044   0.5092   1.0000
   8.500   1.2205   0.07399   0.06601  -0.1014   0.4960   1.0000
   8.750   1.3234   0.06508   0.05762  -0.0972   0.4784   1.0000
   9.000   1.2571   0.07720   0.06947  -0.0997   0.4622   1.0000
   9.250   1.2507   0.08080   0.07318  -0.0978   0.4469   1.0000
   9.500   1.2407   0.08565   0.07807  -0.0979   0.4303   1.0000
   9.750   1.2521   0.08663   0.07934  -0.0947   0.4141   1.0000
  10.000   1.4430   0.05490   0.04895  -0.0711   0.3841   1.0000
  10.250   1.4627   0.04953   0.04372  -0.0574   0.3644   1.0000
  10.500   1.5153   0.04743   0.04155  -0.0518   0.3056   0.9870
  10.750   1.5110   0.04636   0.04049  -0.0475   0.2837   0.9909
  11.000   1.5073   0.04666   0.04069  -0.0424   0.2576   0.9925
  11.250   1.5020   0.04683   0.04068  -0.0386   0.2371   1.0000
  11.500   1.5064   0.04861   0.04224  -0.0367   0.2092   1.0000
  11.750   1.5321   0.05222   0.04545  -0.0413   0.1721   1.0000
  12.000   1.5414   0.05643   0.04971  -0.0432   0.1489   1.0000
  12.250   1.5549   0.06072   0.05383  -0.0440   0.1285   1.0000
  12.500   1.5585   0.06502   0.05821  -0.0436   0.1154   1.0000
  12.750   1.5660   0.06978   0.06299  -0.0435   0.1037   1.0000
  13.000   1.5480   0.07451   0.06817  -0.0429   0.1014   1.0000
  13.250   1.5306   0.07966   0.07365  -0.0429   0.0990   1.0000
  13.500   1.5373   0.08450   0.07845  -0.0420   0.0910   1.0000
  13.750   1.5165   0.09050   0.08474  -0.0433   0.0908   1.0000
  14.000   1.4941   0.09661   0.09113  -0.0443   0.0908   1.0000
  14.250   1.4712   0.10331   0.09807  -0.0463   0.0911   1.0000
  14.500   1.4484   0.11045   0.10543  -0.0488   0.0915   1.0000
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