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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 100,000
Max Cl/Cd: 66.82 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e377-il-100000-n5.txt
Download as CSV file: xf-e377-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.2079   0.10623   0.10183  -0.0162   1.0000   0.0205
  -7.750  -0.1997   0.10427   0.09995  -0.0172   1.0000   0.0210
  -7.500  -0.1928   0.10275   0.09852  -0.0183   1.0000   0.0214
  -7.250  -0.1792   0.10091   0.09676  -0.0213   0.9698   0.0216
  -7.000  -0.1482   0.09830   0.09410  -0.0294   0.9235   0.0218
  -6.750  -0.1210   0.09606   0.09177  -0.0361   0.8884   0.0220
  -6.500  -0.0989   0.09398   0.08959  -0.0408   0.8559   0.0220
  -6.250  -0.0796   0.09200   0.08750  -0.0444   0.8296   0.0221
  -6.000  -0.0765   0.08475   0.08023  -0.0402   0.8152   0.0229
  -5.750  -0.0638   0.08171   0.07710  -0.0407   0.7963   0.0240
  -5.500  -0.0477   0.07925   0.07457  -0.0426   0.7829   0.0258
  -5.250  -0.0295   0.07691   0.07216  -0.0451   0.7684   0.0275
  -5.000  -0.0075   0.07476   0.06992  -0.0486   0.7561   0.0294
  -4.750   0.0241   0.07375   0.06879  -0.0549   0.7426   0.0306
  -4.500   0.0601   0.07277   0.06770  -0.0624   0.7316   0.0309
  -4.250   0.0950   0.07110   0.06592  -0.0688   0.7215   0.0311
  -4.000   0.0942   0.06500   0.05983  -0.0644   0.7134   0.0319
  -3.750   0.1120   0.06177   0.05657  -0.0653   0.7042   0.0331
  -3.500   0.1368   0.05920   0.05390  -0.0680   0.6962   0.0348
  -3.250   0.1661   0.05677   0.05140  -0.0718   0.6878   0.0369
  -3.000   0.2311   0.05720   0.05152  -0.0838   0.6793   0.0416
  -2.750   0.2627   0.05393   0.04817  -0.0877   0.6721   0.0422
  -2.500   0.2752   0.04975   0.04400  -0.0868   0.6654   0.0433
  -2.250   0.3011   0.04709   0.04126  -0.0887   0.6582   0.0452
  -2.000   0.3338   0.04487   0.03892  -0.0919   0.6515   0.0475
  -1.750   0.3702   0.04282   0.03673  -0.0957   0.6445   0.0504
  -1.500   0.4215   0.04185   0.03549  -0.1021   0.6382   0.0542
  -1.000   0.4841   0.03694   0.03034  -0.1068   0.6262   0.0575
  -0.750   0.5156   0.03522   0.02855  -0.1088   0.6192   0.0623
  -0.500   0.5529   0.03362   0.02674  -0.1115   0.6137   0.0645
   0.000   0.6346   0.02925   0.02182  -0.1176   0.6020   0.0399
   0.250   0.6684   0.02768   0.02003  -0.1191   0.5971   0.0384
   0.500   0.7035   0.02615   0.01830  -0.1208   0.5909   0.0375
   0.750   0.7385   0.02462   0.01648  -0.1221   0.5859   0.0373
   1.000   0.7744   0.02292   0.01444  -0.1234   0.5807   0.0402
   1.250   0.8054   0.02196   0.01328  -0.1240   0.5750   0.0452
   1.500   0.8377   0.02059   0.01149  -0.1244   0.5705   0.0483
   1.750   0.8700   0.01908   0.00944  -0.1249   0.5651   0.0557
   2.000   0.8971   0.01906   0.00938  -0.1246   0.5596   0.0723
   2.250   0.9246   0.01912   0.00921  -0.1244   0.5552   0.0947
   2.500   0.9526   0.01912   0.00915  -0.1244   0.5490   0.1078
   2.750   0.9809   0.01901   0.00897  -0.1243   0.5440   0.1142
   3.000   1.0087   0.01890   0.00870  -0.1241   0.5392   0.1224
   3.250   1.0353   0.01898   0.00878  -0.1239   0.5333   0.1352
   3.500   1.0617   0.01901   0.00875  -0.1234   0.5287   0.1480
   3.750   1.0879   0.01911   0.00886  -0.1231   0.5234   0.1610
   4.000   1.1138   0.01926   0.00913  -0.1228   0.5178   0.1798
   4.250   1.1399   0.01938   0.00920  -0.1223   0.5134   0.2004
   4.500   1.1655   0.01961   0.00957  -0.1220   0.5072   0.2248
   4.750   1.1912   0.01978   0.00979  -0.1216   0.5018   0.2522
   5.000   1.2170   0.01995   0.01010  -0.1212   0.4965   0.2899
   5.250   1.2423   0.02007   0.01049  -0.1209   0.4898   0.3753
   5.500   1.2699   0.01975   0.01058  -0.1207   0.4845   1.0000
   5.750   1.2946   0.02012   0.01105  -0.1203   0.4766   1.0000
   6.000   1.3200   0.02031   0.01120  -0.1197   0.4705   1.0000
   6.250   1.3442   0.02067   0.01177  -0.1192   0.4618   1.0000
   6.500   1.3691   0.02089   0.01202  -0.1185   0.4546   1.0000
   6.750   1.3932   0.02119   0.01244  -0.1179   0.4456   1.0000
   7.000   1.4172   0.02148   0.01286  -0.1173   0.4366   1.0000
   7.250   1.4414   0.02168   0.01311  -0.1165   0.4276   1.0000
   7.500   1.4646   0.02199   0.01358  -0.1158   0.4164   1.0000
   7.750   1.4875   0.02230   0.01413  -0.1150   0.4043   1.0000
   8.000   1.5101   0.02260   0.01460  -0.1142   0.3910   1.0000
   8.250   1.5321   0.02294   0.01508  -0.1133   0.3762   1.0000
   8.500   1.5534   0.02331   0.01558  -0.1123   0.3596   1.0000
   8.750   1.5735   0.02381   0.01623  -0.1112   0.3396   1.0000
   9.000   1.5923   0.02440   0.01690  -0.1100   0.3168   1.0000
   9.250   1.6090   0.02520   0.01783  -0.1087   0.2888   1.0000
   9.500   1.6226   0.02629   0.01891  -0.1071   0.2554   1.0000
   9.750   1.6297   0.02794   0.02035  -0.1051   0.2151   1.0000
  10.000   1.6315   0.03001   0.02221  -0.1028   0.1792   1.0000
  10.250   1.6299   0.03227   0.02431  -0.1003   0.1477   1.0000
  10.500   1.6238   0.03458   0.02653  -0.0974   0.1260   1.0000
  10.750   1.6175   0.03699   0.02895  -0.0950   0.1104   1.0000
  11.000   1.6111   0.03978   0.03177  -0.0934   0.0972   1.0000
  11.250   1.6029   0.04309   0.03509  -0.0924   0.0826   1.0000
  11.500   1.5933   0.04686   0.03883  -0.0918   0.0676   1.0000
  11.750   1.5836   0.05089   0.04284  -0.0916   0.0543   1.0000
  12.000   1.5741   0.05508   0.04705  -0.0915   0.0429   1.0000
  12.250   1.5640   0.05951   0.05152  -0.0917   0.0334   1.0000
  12.500   1.5531   0.06418   0.05623  -0.0920   0.0262   1.0000
  12.750   1.5408   0.06919   0.06125  -0.0925   0.0212   1.0000
  13.000   1.5311   0.07398   0.06618  -0.0931   0.0179   1.0000
  13.250   1.5211   0.07893   0.07126  -0.0939   0.0157   1.0000
  13.500   1.5098   0.08422   0.07673  -0.0949   0.0143   1.0000
  13.750   1.4990   0.08973   0.08237  -0.0963   0.0132   1.0000
  14.000   1.4908   0.09495   0.08779  -0.0976   0.0124   1.0000
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