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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 100,000
Max Cl/Cd: 61.58 at α=9.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377m-il-100000.txt
Download as CSV file: xf-e377m-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 377 (MODIFIED) 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.1488   0.09710   0.09317  -0.0219   1.0000   0.0263
  -8.000  -0.1431   0.09400   0.09016  -0.0221   1.0000   0.0268
  -7.750  -0.1427   0.09206   0.08835  -0.0215   1.0000   0.0273
  -7.500  -0.1551   0.09227   0.08875  -0.0192   0.9948   0.0275
  -7.250  -0.1269   0.08731   0.08377  -0.0256   0.9830   0.0286
  -7.000  -0.0983   0.08259   0.07903  -0.0321   0.9709   0.0299
  -6.750  -0.0684   0.07806   0.07447  -0.0387   0.9568   0.0318
  -6.500  -0.1720   0.09478   0.09107  -0.0224   0.9858   0.0282
  -6.250  -0.1318   0.09030   0.08656  -0.0313   0.9730   0.0299
  -6.000  -0.0892   0.08610   0.08231  -0.0405   0.9605   0.0324
  -5.750  -0.0351   0.08396   0.08009  -0.0530   0.9439   0.0349
  -5.500   0.0275   0.08455   0.08052  -0.0683   0.9252   0.0355
  -5.250   0.0418   0.07789   0.07384  -0.0686   0.9094   0.0361
  -5.000   0.0523   0.07286   0.06879  -0.0677   0.8921   0.0370
  -4.750   0.0705   0.06986   0.06573  -0.0691   0.8751   0.0385
  -4.500   0.0917   0.06746   0.06326  -0.0712   0.8589   0.0403
  -4.250   0.1145   0.06527   0.06098  -0.0737   0.8442   0.0423
  -4.000   0.1401   0.06331   0.05893  -0.0767   0.8304   0.0446
  -3.750   0.1818   0.06329   0.05874  -0.0831   0.8170   0.0467
  -3.500   0.2245   0.06307   0.05835  -0.0897   0.8051   0.0473
  -3.250   0.2249   0.05712   0.05242  -0.0865   0.7961   0.0487
  -3.000   0.2456   0.05451   0.04976  -0.0877   0.7852   0.0517
  -2.750   0.2753   0.05257   0.04771  -0.0906   0.7756   0.0553
  -2.500   0.3342   0.05414   0.04895  -0.0986   0.7662   0.0587
  -2.250   0.3523   0.04993   0.04476  -0.0994   0.7568   0.0596
  -2.000   0.3713   0.04670   0.04147  -0.0997   0.7494   0.0617
  -1.750   0.4011   0.04483   0.03951  -0.1020   0.7406   0.0652
  -1.500   0.4528   0.04590   0.04028  -0.1073   0.7320   0.0700
  -1.250   0.4723   0.04201   0.03638  -0.1079   0.7249   0.0719
  -1.000   0.4993   0.04007   0.03438  -0.1094   0.7172   0.0764
  -0.750   0.5485   0.04145   0.03540  -0.1130   0.7097   0.0815
  -0.500   0.5719   0.03814   0.03210  -0.1142   0.7024   0.0828
  -0.250   0.5980   0.03606   0.02993  -0.1151   0.6959   0.0859
   0.000   0.6306   0.03521   0.02895  -0.1167   0.6888   0.0908
   0.250   0.6713   0.03575   0.02920  -0.1185   0.6819   0.0937
   0.500   0.6935   0.03298   0.02645  -0.1192   0.6757   0.0976
   0.750   0.7317   0.03402   0.02721  -0.1202   0.6685   0.1052
   1.000   0.7580   0.03164   0.02474  -0.1210   0.6634   0.1071
   1.250   0.7860   0.03059   0.02366  -0.1218   0.6560   0.1115
   1.500   0.8224   0.03148   0.02419  -0.1219   0.6507   0.1175
   1.750   0.8462   0.02937   0.02217  -0.1229   0.6437   0.1236
   2.000   0.8761   0.02875   0.02138  -0.1231   0.6381   0.1346
   2.250   0.9052   0.02830   0.02079  -0.1234   0.6320   0.1458
   2.500   0.9334   0.02780   0.02016  -0.1236   0.6257   0.1714
   2.750   0.9623   0.02730   0.01941  -0.1234   0.6213   0.2025
   3.000   0.9860   0.02656   0.01873  -0.1241   0.6138   0.2729
   3.250   1.0123   0.02570   0.01774  -0.1240   0.6087   0.3393
   3.500   1.0378   0.02559   0.01765  -0.1241   0.6022   0.3760
   3.750   1.0668   0.02536   0.01732  -0.1243   0.5961   0.4109
   4.000   1.0953   0.02546   0.01730  -0.1240   0.5909   0.4125
   4.250   1.1211   0.02615   0.01799  -0.1239   0.5833   0.3953
   4.500   1.1494   0.02640   0.01809  -0.1231   0.5786   0.3668
   4.750   1.1733   0.02727   0.01904  -0.1228   0.5705   0.3443
   5.000   1.2007   0.02749   0.01921  -0.1220   0.5651   0.3180
   5.250   1.2240   0.02826   0.02006  -0.1215   0.5571   0.3014
   5.500   1.2506   0.02830   0.02004  -0.1207   0.5512   0.2959
   5.750   1.2731   0.02892   0.02077  -0.1200   0.5429   0.2925
   6.000   1.2995   0.02883   0.02066  -0.1190   0.5366   0.2836
   6.250   1.3215   0.02948   0.02148  -0.1183   0.5278   0.2782
   6.500   1.3485   0.02917   0.02115  -0.1172   0.5215   0.2747
   6.750   1.3697   0.02976   0.02190  -0.1164   0.5117   0.2745
   7.000   1.3979   0.02928   0.02135  -0.1154   0.5054   0.2804
   7.250   1.4193   0.02967   0.02192  -0.1145   0.4947   0.2810
   7.500   1.4425   0.02981   0.02218  -0.1134   0.4848   0.2808
   7.750   1.4713   0.02910   0.02148  -0.1124   0.4766   0.2822
   8.000   1.4941   0.02906   0.02161  -0.1113   0.4648   0.2849
   8.250   1.5172   0.02894   0.02164  -0.1101   0.4524   0.2899
   8.500   1.5411   0.02862   0.02146  -0.1089   0.4395   0.3031
   8.750   1.5652   0.02818   0.02116  -0.1076   0.4253   0.3180
   9.000   1.5864   0.02736   0.02097  -0.1059   0.4102   0.7753
   9.250   1.6126   0.02667   0.02044  -0.1050   0.3921   1.0000
   9.500   1.6302   0.02672   0.02072  -0.1032   0.3697   1.0000
   9.750   1.6473   0.02675   0.02086  -0.1013   0.3434   1.0000
  10.000   1.6604   0.02718   0.02133  -0.0991   0.3109   1.0000
  10.250   1.6671   0.02821   0.02226  -0.0964   0.2709   1.0000
  10.500   1.6662   0.02999   0.02379  -0.0934   0.2308   1.0000
  10.750   1.6599   0.03222   0.02586  -0.0901   0.1993   1.0000
  11.000   1.6489   0.03458   0.02810  -0.0865   0.1769   1.0000
  11.250   1.6367   0.03735   0.03081  -0.0838   0.1581   1.0000
  11.500   1.6246   0.04060   0.03401  -0.0821   0.1421   1.0000
  11.750   1.6121   0.04432   0.03768  -0.0810   0.1273   1.0000
  12.000   1.6003   0.04834   0.04170  -0.0806   0.1123   1.0000
  12.250   1.5873   0.05279   0.04617  -0.0804   0.0983   1.0000
  12.500   1.5722   0.05772   0.05108  -0.0806   0.0844   1.0000
  12.750   1.5548   0.06318   0.05650  -0.0809   0.0706   1.0000
  13.000   1.5365   0.06891   0.06218  -0.0813   0.0584   1.0000
  13.250   1.5208   0.07433   0.06751  -0.0817   0.0499   1.0000
  13.500   1.5096   0.07940   0.07263  -0.0822   0.0425   1.0000
  13.750   1.5037   0.08358   0.07685  -0.0819   0.0374   1.0000
  14.000   1.5004   0.08761   0.08096  -0.0820   0.0336   1.0000
  14.250   1.5050   0.09002   0.08321  -0.0794   0.0301   1.0000
  14.500   1.5099   0.09317   0.08663  -0.0785   0.0287   1.0000
  14.750   1.5136   0.09670   0.09040  -0.0778   0.0275   1.0000
  15.000   1.5137   0.10093   0.09489  -0.0777   0.0268   1.0000
  15.250   1.5099   0.10589   0.10011  -0.0784   0.0263   1.0000
  15.500   1.5026   0.11150   0.10599  -0.0800   0.0261   1.0000
  15.750   1.4920   0.11774   0.11251  -0.0824   0.0260   1.0000
  16.000   1.4791   0.12456   0.11959  -0.0855   0.0261   1.0000
  16.250   1.4646   0.13197   0.12727  -0.0895   0.0262   1.0000
  16.500   1.4486   0.13996   0.13550  -0.0942   0.0264   1.0000
  16.750   1.4320   0.14854   0.14430  -0.0997   0.0268   1.0000
  17.000   1.4142   0.15791   0.15388  -0.1061   0.0272   1.0000
  17.250   1.3962   0.16796   0.16409  -0.1131   0.0277   1.0000
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