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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 1,000,000
Max Cl/Cd: 140.98 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377-il-1000000-n5.txt
Download as CSV file: xf-e377-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1679   0.09596   0.09304  -0.0252   0.6181   0.0032
  -7.500  -0.1595   0.09361   0.09067  -0.0262   0.6111   0.0031
  -7.250  -0.1521   0.09112   0.08818  -0.0267   0.6045   0.0032
  -6.750  -0.1314   0.08673   0.08377  -0.0292   0.5917   0.0039
  -6.500  -0.1175   0.08470   0.08171  -0.0308   0.5853   0.0054
  -6.250  -0.1024   0.08205   0.07906  -0.0331   0.5798   0.0056
  -6.000  -0.0869   0.07947   0.07646  -0.0355   0.5736   0.0056
  -5.750  -0.0693   0.07691   0.07387  -0.0382   0.5690   0.0056
  -5.500  -0.0501   0.07427   0.07122  -0.0413   0.5635   0.0057
  -5.250  -0.0302   0.07159   0.06851  -0.0443   0.5584   0.0057
  -4.750   0.0115   0.06593   0.06279  -0.0504   0.5492   0.0056
  -4.500   0.0324   0.06333   0.06017  -0.0531   0.5446   0.0053
  -4.250   0.0574   0.06061   0.05741  -0.0567   0.5403   0.0049
  -4.000   0.0849   0.05764   0.05441  -0.0608   0.5358   0.0047
  -3.750   0.1143   0.05465   0.05138  -0.0651   0.5312   0.0046
  -3.500   0.1457   0.05160   0.04827  -0.0696   0.5271   0.0048
  -3.250   0.1866   0.04716   0.04377  -0.0766   0.5237   0.0059
  -3.000   0.2147   0.04549   0.04206  -0.0792   0.5191   0.0062
  -2.750   0.2447   0.04380   0.04031  -0.0821   0.5145   0.0071
  -2.500   0.2803   0.04126   0.03770  -0.0863   0.5105   0.0079
  -2.250   0.3183   0.03844   0.03481  -0.0909   0.5066   0.0077
  -2.000   0.3598   0.03535   0.03163  -0.0959   0.5024   0.0083
  -1.750   0.4037   0.03220   0.02835  -0.1012   0.4984   0.0096
  -1.500   0.4323   0.03117   0.02728  -0.1027   0.4943   0.0104
  -1.250   0.4651   0.02986   0.02590  -0.1049   0.4900   0.0128
  -1.000   0.5044   0.02736   0.02328  -0.1084   0.4860   0.0112
  -0.750   0.5535   0.02328   0.01898  -0.1135   0.4826   0.0099
  -0.500   0.5896   0.02134   0.01692  -0.1157   0.4784   0.0103
  -0.250   0.6245   0.01962   0.01507  -0.1175   0.4743   0.0112
   0.000   0.6799   0.01079   0.00531  -0.1232   0.4717   0.0119
   0.250   0.7088   0.00989   0.00416  -0.1233   0.4680   0.0123
   0.500   0.7370   0.00935   0.00344  -0.1233   0.4636   0.0127
   0.750   0.7651   0.00888   0.00278  -0.1231   0.4593   0.0126
   1.000   0.7928   0.00858   0.00235  -0.1229   0.4555   0.0127
   1.250   0.8206   0.00836   0.00205  -0.1227   0.4516   0.0128
   1.500   0.8481   0.00822   0.00184  -0.1225   0.4470   0.0131
   1.750   0.8755   0.00815   0.00171  -0.1222   0.4427   0.0137
   2.000   0.9030   0.00811   0.00164  -0.1220   0.4389   0.0144
   2.250   0.9304   0.00806   0.00154  -0.1218   0.4343   0.0173
   2.500   0.9577   0.00807   0.00153  -0.1215   0.4297   0.0212
   2.750   0.9849   0.00804   0.00158  -0.1213   0.4254   0.0428
   3.000   1.0121   0.00808   0.00163  -0.1211   0.4198   0.0532
   3.250   1.0391   0.00815   0.00169  -0.1209   0.4138   0.0601
   3.500   1.0663   0.00819   0.00176  -0.1207   0.4074   0.0708
   4.000   1.1202   0.00835   0.00193  -0.1203   0.3934   0.0909
   4.500   1.1739   0.00854   0.00213  -0.1199   0.3795   0.1087
   4.750   1.2006   0.00867   0.00226  -0.1196   0.3717   0.1190
   5.000   1.2273   0.00878   0.00240  -0.1194   0.3629   0.1302
   5.250   1.2538   0.00892   0.00255  -0.1192   0.3537   0.1458
   5.500   1.2801   0.00908   0.00272  -0.1190   0.3433   0.1635
   5.750   1.3063   0.00927   0.00291  -0.1188   0.3307   0.1790
   6.000   1.3323   0.00948   0.00311  -0.1185   0.3171   0.1994
   6.250   1.3581   0.00974   0.00337  -0.1183   0.3008   0.2210
   6.500   1.3832   0.01009   0.00366  -0.1180   0.2776   0.2447
   6.750   1.4061   0.01081   0.00417  -0.1176   0.2305   0.2804
   7.000   1.4287   0.01144   0.00480  -0.1172   0.1884   0.5207
   7.500   1.4722   0.01261   0.00615  -0.1162   0.1028   1.0000
   7.750   1.4927   0.01359   0.00689  -0.1155   0.0657   1.0000
   8.000   1.5141   0.01435   0.00752  -0.1148   0.0441   1.0000
   8.250   1.5334   0.01539   0.00839  -0.1139   0.0183   1.0000
   8.500   1.5523   0.01642   0.00932  -0.1129   0.0033   1.0000
   8.750   1.5744   0.01695   0.00990  -0.1122   0.0025   1.0000
   9.000   1.5957   0.01755   0.01059  -0.1114   0.0021   1.0000
   9.250   1.6160   0.01824   0.01136  -0.1105   0.0017   1.0000
   9.500   1.6362   0.01887   0.01205  -0.1096   0.0015   1.0000
   9.750   1.6559   0.01951   0.01275  -0.1087   0.0014   1.0000
  10.000   1.6743   0.02024   0.01355  -0.1076   0.0014   1.0000
  10.250   1.6913   0.02104   0.01443  -0.1064   0.0013   1.0000
  10.500   1.7071   0.02188   0.01535  -0.1050   0.0012   1.0000
  10.750   1.7205   0.02285   0.01642  -0.1033   0.0012   1.0000
  11.000   1.7318   0.02386   0.01752  -0.1015   0.0011   1.0000
  11.250   1.7371   0.02491   0.01866  -0.0986   0.0010   1.0000
  11.500   1.7390   0.02617   0.02001  -0.0957   0.0010   1.0000
  11.750   1.7397   0.02777   0.02171  -0.0934   0.0009   1.0000
  12.000   1.7410   0.02960   0.02364  -0.0916   0.0009   1.0000
  12.250   1.7419   0.03174   0.02587  -0.0904   0.0008   1.0000
  12.500   1.7414   0.03426   0.02850  -0.0894   0.0008   1.0000
  12.750   1.7404   0.03700   0.03135  -0.0888   0.0008   1.0000
  13.000   1.7375   0.04011   0.03458  -0.0883   0.0007   1.0000
  13.250   1.7312   0.04379   0.03838  -0.0881   0.0007   1.0000
  13.500   1.7221   0.04797   0.04269  -0.0882   0.0006   1.0000
  13.750   1.7063   0.05317   0.04806  -0.0885   0.0006   1.0000
  14.000   1.6938   0.05810   0.05313  -0.0890   0.0006   1.0000
  14.250   1.6838   0.06277   0.05792  -0.0896   0.0006   1.0000
  14.500   1.6756   0.06736   0.06263  -0.0903   0.0006   1.0000
  14.750   1.6677   0.07206   0.06744  -0.0912   0.0006   1.0000
  15.000   1.6647   0.07615   0.07164  -0.0921   0.0006   1.0000
  15.250   1.6543   0.08161   0.07723  -0.0936   0.0006   1.0000
  15.500   1.6471   0.08665   0.08240  -0.0950   0.0005   1.0000
  15.750   1.6395   0.09188   0.08776  -0.0965   0.0005   1.0000
  16.000   1.6309   0.09745   0.09344  -0.0983   0.0005   1.0000
  16.250   1.6220   0.10319   0.09931  -0.1003   0.0005   1.0000
  16.500   1.6128   0.10910   0.10534  -0.1025   0.0005   1.0000
  16.750   1.6029   0.11529   0.11165  -0.1050   0.0005   1.0000
  17.000   1.5938   0.12140   0.11788  -0.1075   0.0005   1.0000
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