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EPPLER 377 (MODIFIED) AIRFOIL (e377m-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 (MODIFIED) AIRFOIL (e377m-il)
Reynolds number: 1,000,000
Max Cl/Cd: 142.56 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377m-il-1000000.txt
Download as CSV file: xf-e377m-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.250  -0.1108   0.07719   0.07477  -0.0245   0.6685   0.0055
  -7.000  -0.1040   0.07459   0.07214  -0.0250   0.6585   0.0056
  -6.750  -0.0949   0.07200   0.06952  -0.0260   0.6485   0.0057
  -6.500  -0.0834   0.06929   0.06678  -0.0275   0.6393   0.0058
  -6.250  -0.0709   0.06657   0.06404  -0.0292   0.6308   0.0060
  -6.000  -0.0577   0.06381   0.06124  -0.0311   0.6227   0.0061
  -5.750  -0.0430   0.06098   0.05839  -0.0331   0.6159   0.0062
  -5.500  -0.0275   0.05813   0.05551  -0.0353   0.6088   0.0066
  -5.250  -0.0104   0.05519   0.05254  -0.0377   0.6025   0.0069
  -5.000   0.0070   0.06826   0.06541  -0.0499   0.6137   0.0068
  -4.750   0.0297   0.06567   0.06277  -0.0529   0.6066   0.0074
  -4.500   0.0557   0.06302   0.06008  -0.0564   0.5997   0.0080
  -4.250   0.0840   0.06041   0.05741  -0.0604   0.5931   0.0081
  -4.000   0.1135   0.05768   0.05464  -0.0645   0.5870   0.0082
  -3.750   0.1445   0.05485   0.05174  -0.0687   0.5810   0.0082
  -3.500   0.1703   0.05122   0.04808  -0.0720   0.5760   0.0086
  -3.250   0.1973   0.04913   0.04595  -0.0747   0.5703   0.0090
  -3.000   0.2266   0.04709   0.04383  -0.0776   0.5647   0.0098
  -2.750   0.2591   0.04481   0.04150  -0.0811   0.5596   0.0112
  -2.500   0.2972   0.04267   0.03928  -0.0852   0.5545   0.0118
  -2.250   0.3327   0.04044   0.03695  -0.0888   0.5496   0.0119
  -2.000   0.3681   0.03806   0.03452  -0.0921   0.5451   0.0120
  -1.750   0.4061   0.03435   0.03070  -0.0965   0.5405   0.0125
  -1.500   0.4326   0.03301   0.02930  -0.0977   0.5356   0.0133
  -1.250   0.4647   0.03144   0.02767  -0.0998   0.5315   0.0147
  -1.000   0.5026   0.03014   0.02628  -0.1023   0.5268   0.0172
  -0.750   0.5368   0.02850   0.02454  -0.1043   0.5222   0.0174
  -0.500   0.5707   0.02674   0.02268  -0.1062   0.5181   0.0174
  -0.250   0.6050   0.02488   0.02073  -0.1080   0.5140   0.0175
   1.000   0.7819   0.01152   0.00612  -0.1158   0.4942   0.0180
   1.250   0.8114   0.00970   0.00387  -0.1160   0.4902   0.0195
   1.500   0.8391   0.00925   0.00334  -0.1158   0.4859   0.0214
   1.750   0.8664   0.00898   0.00298  -0.1156   0.4816   0.0229
   2.000   0.8935   0.00881   0.00272  -0.1154   0.4771   0.0248
   2.250   0.9198   0.00806   0.00203  -0.1151   0.4733   0.0571
   2.500   0.9470   0.00814   0.00214  -0.1149   0.4687   0.0732
   2.750   0.9745   0.00841   0.00240  -0.1147   0.4640   0.0784
   3.000   1.0019   0.00860   0.00260  -0.1145   0.4595   0.0817
   3.250   1.0296   0.00904   0.00310  -0.1143   0.4542   0.0840
   3.500   1.0565   0.00935   0.00340  -0.1141   0.4485   0.0848
   3.750   1.0837   0.00945   0.00354  -0.1139   0.4431   0.0863
   4.000   1.1105   0.00958   0.00365  -0.1137   0.4371   0.0890
   4.250   1.1372   0.00929   0.00330  -0.1135   0.4318   0.0946
   4.500   1.1642   0.00936   0.00340  -0.1133   0.4261   0.0957
   4.750   1.1907   0.00952   0.00354  -0.1131   0.4200   0.0970
   5.000   1.2176   0.00960   0.00368  -0.1129   0.4142   0.0989
   5.250   1.2440   0.00958   0.00363  -0.1127   0.4074   0.1008
   5.500   1.2705   0.00948   0.00353  -0.1125   0.4011   0.1036
   5.750   1.2968   0.00948   0.00350  -0.1123   0.3937   0.1062
   6.000   1.3232   0.00955   0.00361  -0.1121   0.3863   0.1081
   6.500   1.3755   0.00976   0.00387  -0.1117   0.3686   0.1109
   6.750   1.4014   0.00987   0.00398  -0.1114   0.3586   0.1124
   7.000   1.4270   0.01001   0.00410  -0.1112   0.3481   0.1138
   7.250   1.4524   0.01019   0.00426  -0.1109   0.3313   0.1154
   7.500   1.4761   0.01066   0.00458  -0.1105   0.2957   0.1168
   7.750   1.4973   0.01146   0.00507  -0.1099   0.2408   0.1189
   8.000   1.5183   0.01233   0.00571  -0.1092   0.1960   0.1209
   8.250   1.5395   0.01312   0.00632  -0.1086   0.1601   0.1232
   8.500   1.5594   0.01405   0.00703  -0.1078   0.1218   0.1249
   8.750   1.5786   0.01501   0.00779  -0.1070   0.0889   0.1267
   9.000   1.5963   0.01610   0.00867  -0.1059   0.0552   0.1280
   9.250   1.6074   0.01791   0.01013  -0.1041   0.0125   0.1289
   9.500   1.6238   0.01894   0.01115  -0.1028   0.0044   0.1307
   9.750   1.6425   0.01966   0.01196  -0.1016   0.0036   0.1327
  10.000   1.6597   0.02048   0.01290  -0.1003   0.0032   0.1349
  10.250   1.6757   0.02133   0.01385  -0.0989   0.0031   0.1372
  10.500   1.6907   0.02217   0.01481  -0.0974   0.0030   0.1397
  10.750   1.7031   0.02312   0.01585  -0.0956   0.0028   0.1422
  11.000   1.7107   0.02417   0.01702  -0.0930   0.0027   0.1443
  11.250   1.7110   0.02537   0.01832  -0.0895   0.0025   0.1456
  11.500   1.7104   0.02683   0.01989  -0.0864   0.0024   0.1471
  11.750   1.7085   0.02869   0.02185  -0.0840   0.0023   0.1484
  12.000   1.7057   0.03093   0.02421  -0.0821   0.0022   0.1501
  12.250   1.6997   0.03382   0.02722  -0.0806   0.0021   0.1509
  12.500   1.6956   0.03679   0.03031  -0.0798   0.0020   0.1520
  12.750   1.6930   0.03979   0.03344  -0.0792   0.0021   0.1538
  13.000   1.6839   0.04376   0.03754  -0.0789   0.0020   0.1551
  13.250   1.6755   0.04780   0.04171  -0.0789   0.0019   0.1565
  13.500   1.6673   0.05198   0.04603  -0.0790   0.0019   0.1578
  13.750   1.6608   0.05601   0.05018  -0.0794   0.0019   0.1597
  14.000   1.6509   0.06063   0.05492  -0.0799   0.0019   0.1609
  14.250   1.6412   0.06537   0.05979  -0.0806   0.0019   0.1622
  14.500   1.6321   0.07021   0.06475  -0.0815   0.0019   0.1633
  14.750   1.6253   0.07487   0.06953  -0.0825   0.0019   0.1653
  15.000   1.6187   0.07966   0.07444  -0.0836   0.0019   0.1678
  15.250   1.6125   0.08449   0.07939  -0.0849   0.0019   0.1704
  15.500   1.6051   0.08964   0.08467  -0.0863   0.0019   0.1728
  15.750   1.5989   0.09471   0.08987  -0.0878   0.0020   0.1753
  16.000   1.5925   0.09990   0.09519  -0.0894   0.0020   0.1777
  16.250   1.5860   0.10521   0.10065  -0.0911   0.0020   0.1813
  16.500   1.5784   0.11081   0.10641  -0.0930   0.0021   0.1846
  16.750   1.5694   0.11673   0.11251  -0.0950   0.0022   0.1876
  17.000   1.5578   0.12335   0.11934  -0.0974   0.0024   0.1902
  17.250   1.5460   0.13019   0.12637  -0.1003   0.0025   0.1928
  17.500   1.5341   0.13727   0.13363  -0.1037   0.0026   0.1964
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