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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 50,000
Max Cl/Cd: 38.95 at α=9.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e376-il-50000-n5.txt
Download as CSV file: xf-e376-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 376 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.2321   0.10939   0.10322  -0.0136   1.0000   0.0251
  -8.000  -0.2243   0.10725   0.10118  -0.0146   1.0000   0.0258
  -7.750  -0.2165   0.10524   0.09926  -0.0156   1.0000   0.0267
  -7.500  -0.2072   0.10327   0.09738  -0.0171   1.0000   0.0274
  -7.250  -0.1974   0.10157   0.09574  -0.0187   1.0000   0.0280
  -7.000  -0.1876   0.10027   0.09456  -0.0206   1.0000   0.0284
  -6.750  -0.1792   0.09947   0.09389  -0.0223   1.0000   0.0287
  -6.500  -0.1764   0.09916   0.09374  -0.0230   1.0000   0.0289
  -6.250  -0.1376   0.09815   0.09270  -0.0331   0.9767   0.0292
  -6.000  -0.1139   0.09175   0.08634  -0.0366   0.9604   0.0296
  -5.750  -0.0916   0.08589   0.08046  -0.0396   0.9443   0.0308
  -5.500  -0.0605   0.08200   0.07653  -0.0453   0.9271   0.0322
  -5.250  -0.0291   0.07874   0.07319  -0.0509   0.9083   0.0338
  -5.000   0.0018   0.07590   0.07028  -0.0562   0.8902   0.0355
  -4.750   0.0340   0.07360   0.06788  -0.0615   0.8730   0.0373
  -4.500   0.0749   0.07286   0.06692  -0.0688   0.8563   0.0386
  -4.250   0.1134   0.07192   0.06584  -0.0753   0.8403   0.0393
  -4.000   0.1186   0.06641   0.06035  -0.0733   0.8275   0.0407
  -3.750   0.1393   0.06351   0.05738  -0.0750   0.8144   0.0430
  -3.500   0.1664   0.06130   0.05507  -0.0780   0.8018   0.0455
  -3.250   0.1974   0.05948   0.05311  -0.0816   0.7897   0.0480
  -3.000   0.2417   0.05917   0.05258  -0.0878   0.7780   0.0501
  -2.750   0.2769   0.05755   0.05081  -0.0918   0.7680   0.0508
  -2.500   0.2914   0.05339   0.04665  -0.0917   0.7582   0.0525
  -2.250   0.3185   0.05110   0.04422  -0.0939   0.7484   0.0554
  -2.000   0.3523   0.04943   0.04239  -0.0971   0.7397   0.0593
  -1.750   0.4013   0.04996   0.04261  -0.1024   0.7300   0.0622
  -1.500   0.4215   0.04631   0.03897  -0.1034   0.7216   0.0640
  -1.250   0.4500   0.04421   0.03674  -0.1051   0.7143   0.0680
  -1.000   0.4926   0.04434   0.03661  -0.1088   0.7050   0.0739
  -0.750   0.5163   0.04141   0.03360  -0.1098   0.6984   0.0786
  -0.500   0.5558   0.04140   0.03337  -0.1126   0.6897   0.0864
  -0.250   0.5811   0.03893   0.03084  -0.1137   0.6832   0.0927
   0.250   0.6458   0.03679   0.02839  -0.1169   0.6688   0.1061
   0.500   0.6787   0.03599   0.02742  -0.1185   0.6613   0.1136
   0.750   0.7127   0.03581   0.02698  -0.1195   0.6550   0.1242
   1.000   0.7400   0.03419   0.02532  -0.1206   0.6477   0.1327
   1.250   0.7712   0.03331   0.02424  -0.1212   0.6425   0.1419
   1.500   0.8016   0.03297   0.02377  -0.1222   0.6347   0.1515
   1.750   0.8310   0.03211   0.02273  -0.1225   0.6293   0.1666
   2.000   0.8576   0.03136   0.02195  -0.1233   0.6221   0.2194
   2.250   0.8969   0.03136   0.02143  -0.1228   0.6165   0.0704
   2.500   0.9273   0.03103   0.02089  -0.1233   0.6100   0.0663
   2.750   0.9585   0.03072   0.02027  -0.1235   0.6038   0.0642
   3.000   0.9886   0.03039   0.01964  -0.1235   0.5984   0.0654
   3.250   1.0171   0.03031   0.01933  -0.1236   0.5913   0.0707
   3.500   1.0450   0.03010   0.01889  -0.1231   0.5866   0.0910
   3.750   1.0702   0.03030   0.01898  -0.1230   0.5791   0.1130
   4.000   1.0960   0.03016   0.01872  -0.1223   0.5738   0.1384
   4.250   1.1196   0.03048   0.01899  -0.1219   0.5671   0.1567
   4.500   1.1440   0.03074   0.01917  -0.1214   0.5611   0.1763
   4.750   1.1681   0.03110   0.01950  -0.1210   0.5551   0.1970
   5.000   1.1914   0.03164   0.02010  -0.1206   0.5481   0.2243
   5.250   1.2169   0.03181   0.02031  -0.1201   0.5428   0.2662
   5.500   1.2385   0.03221   0.02148  -0.1199   0.5345   1.0000
   5.750   1.2643   0.03249   0.02159  -0.1189   0.5295   1.0000
   6.000   1.2837   0.03369   0.02289  -0.1185   0.5202   1.0000
   6.250   1.3077   0.03413   0.02333  -0.1176   0.5138   1.0000
   6.750   1.3489   0.03584   0.02527  -0.1161   0.4963   1.0000
   7.000   1.3732   0.03607   0.02571  -0.1150   0.4887   1.0000
   7.250   1.3910   0.03714   0.02700  -0.1142   0.4783   1.0000
   7.500   1.4122   0.03766   0.02769  -0.1131   0.4691   1.0000
   7.750   1.4368   0.03762   0.02779  -0.1118   0.4601   1.0000
   8.000   1.4543   0.03841   0.02883  -0.1107   0.4481   1.0000
   8.250   1.4726   0.03897   0.02964  -0.1093   0.4358   1.0000
   8.500   1.4920   0.03934   0.03040  -0.1080   0.4229   1.0000
   8.750   1.5107   0.03959   0.03093  -0.1064   0.4090   1.0000
   9.000   1.5289   0.03976   0.03137  -0.1047   0.3938   1.0000
   9.250   1.5474   0.03973   0.03159  -0.1028   0.3772   1.0000
   9.500   1.5588   0.04045   0.03259  -0.1009   0.3580   1.0000
   9.750   1.5690   0.04116   0.03355  -0.0988   0.3369   1.0000
  10.000   1.5747   0.04230   0.03489  -0.0966   0.3140   1.0000
  10.250   1.5780   0.04352   0.03634  -0.0942   0.2903   1.0000
  10.500   1.5739   0.04543   0.03832  -0.0916   0.2672   1.0000
  10.750   1.5671   0.04797   0.04087  -0.0896   0.2454   1.0000
  11.000   1.5591   0.05091   0.04374  -0.0882   0.2240   1.0000
  11.250   1.5483   0.05468   0.04750  -0.0874   0.2037   1.0000
  11.500   1.5367   0.05876   0.05150  -0.0870   0.1848   1.0000
  11.750   1.5241   0.06327   0.05594  -0.0870   0.1668   1.0000
  12.000   1.5108   0.06812   0.06079  -0.0874   0.1493   1.0000
  12.250   1.4969   0.07323   0.06584  -0.0881   0.1330   1.0000
  12.500   1.4824   0.07859   0.07113  -0.0890   0.1178   1.0000
  12.750   1.4677   0.08418   0.07664  -0.0903   0.1033   1.0000
  13.000   1.4541   0.08984   0.08227  -0.0917   0.0891   1.0000
  13.250   1.4407   0.09573   0.08814  -0.0934   0.0755   1.0000
  13.500   1.4280   0.10174   0.09410  -0.0953   0.0635   1.0000
  13.750   1.4166   0.10771   0.10006  -0.0973   0.0544   1.0000
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