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EPPLER 377 AIRFOIL (e377-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 377 AIRFOIL (e377-il)
Reynolds number: 200,000
Max Cl/Cd: 91.3 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e377-il-200000.txt
Download as CSV file: xf-e377-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -7.750  -0.1947   0.10105   0.09802  -0.0179   1.0000   0.0152
  -7.500  -0.1874   0.09891   0.09595  -0.0186   1.0000   0.0155
  -7.250  -0.1820   0.09694   0.09407  -0.0188   1.0000   0.0159
  -7.000  -0.1618   0.09382   0.09101  -0.0232   0.9748   0.0164
  -6.750  -0.1244   0.08952   0.08662  -0.0318   0.9389   0.0171
  -6.500  -0.0916   0.08598   0.08296  -0.0388   0.8979   0.0180
  -6.250  -0.0710   0.08421   0.08106  -0.0425   0.8635   0.0185
  -6.000  -0.0528   0.08317   0.07987  -0.0458   0.8347   0.0188
  -5.750  -0.0328   0.08202   0.07861  -0.0498   0.8139   0.0189
  -5.500  -0.0108   0.08066   0.07711  -0.0541   0.7946   0.0190
  -5.000   0.0146   0.07243   0.06875  -0.0546   0.7684   0.0196
  -4.750   0.0283   0.06916   0.06542  -0.0550   0.7561   0.0202
  -4.500   0.0475   0.06658   0.06276  -0.0571   0.7448   0.0210
  -4.250   0.0695   0.06415   0.06025  -0.0597   0.7342   0.0221
  -4.000   0.0940   0.06178   0.05776  -0.0629   0.7252   0.0236
  -3.750   0.1443   0.06143   0.05729  -0.0725   0.7146   0.0271
  -3.500   0.1902   0.06031   0.05601  -0.0806   0.7056   0.0274
  -3.250   0.2025   0.05520   0.05088  -0.0804   0.6984   0.0280
  -3.000   0.2175   0.05170   0.04737  -0.0802   0.6907   0.0290
  -2.750   0.2440   0.04927   0.04485  -0.0826   0.6836   0.0305
  -2.500   0.2759   0.04701   0.04250  -0.0862   0.6758   0.0325
  -2.250   0.3128   0.04493   0.04029  -0.0905   0.6692   0.0355
  -2.000   0.3797   0.04514   0.04023  -0.1003   0.6614   0.0378
  -1.750   0.3949   0.04039   0.03548  -0.1005   0.6556   0.0393
  -1.500   0.4202   0.03814   0.03319  -0.1018   0.6491   0.0420
  -1.250   0.4554   0.03630   0.03122  -0.1048   0.6426   0.0453
  -1.000   0.5119   0.03631   0.03092  -0.1108   0.6365   0.0498
  -0.750   0.5470   0.03345   0.02796  -0.1138   0.6302   0.0508
  -0.500   0.5695   0.03095   0.02539  -0.1143   0.6251   0.0525
  -0.250   0.6001   0.02940   0.02380  -0.1158   0.6186   0.0558
   1.000   0.7707   0.02307   0.01669  -0.1234   0.5912   0.0802
   1.250   0.8017   0.02211   0.01558  -0.1240   0.5857   0.0851
   1.750   0.8774   0.01736   0.00989  -0.1262   0.5761   0.0590
   2.000   0.9084   0.01592   0.00797  -0.1263   0.5713   0.0662
   2.250   0.9361   0.01589   0.00773  -0.1259   0.5668   0.0896
   2.500   0.9620   0.01622   0.00826  -0.1258   0.5606   0.1106
   2.750   0.9896   0.01600   0.00788  -0.1255   0.5558   0.1204
   3.000   1.0169   0.01587   0.00765  -0.1252   0.5510   0.1269
   3.250   1.0439   0.01573   0.00751  -0.1250   0.5452   0.1340
   3.500   1.0711   0.01571   0.00742  -0.1247   0.5407   0.1454
   3.750   1.0976   0.01578   0.00754  -0.1245   0.5354   0.1598
   4.000   1.1241   0.01580   0.00765  -0.1241   0.5297   0.1753
   4.250   1.1514   0.01589   0.00767  -0.1239   0.5253   0.1956
   4.500   1.1779   0.01599   0.00793  -0.1237   0.5188   0.2194
   4.750   1.2043   0.01602   0.00799  -0.1233   0.5132   0.2452
   5.000   1.2305   0.01612   0.00814  -0.1229   0.5075   0.2783
   5.250   1.2567   0.01613   0.00832  -0.1226   0.5007   0.3246
   5.500   1.2858   0.01556   0.00837  -0.1229   0.4950   1.0000
   5.750   1.3115   0.01574   0.00860  -0.1225   0.4874   1.0000
   6.000   1.3377   0.01591   0.00867  -0.1220   0.4817   1.0000
   6.250   1.3628   0.01608   0.00897  -0.1215   0.4735   1.0000
   6.500   1.3886   0.01622   0.00912  -0.1210   0.4669   1.0000
   6.750   1.4136   0.01636   0.00937  -0.1205   0.4580   1.0000
   7.000   1.4388   0.01650   0.00957  -0.1200   0.4497   1.0000
   7.250   1.4639   0.01660   0.00970  -0.1194   0.4408   1.0000
   7.500   1.4883   0.01673   0.00997  -0.1188   0.4304   1.0000
   7.750   1.5127   0.01687   0.01024  -0.1182   0.4197   1.0000
   8.000   1.5368   0.01700   0.01046  -0.1175   0.4080   1.0000
   8.250   1.5604   0.01716   0.01072  -0.1168   0.3947   1.0000
   8.500   1.5836   0.01735   0.01105  -0.1160   0.3790   1.0000
   8.750   1.6059   0.01759   0.01137  -0.1152   0.3583   1.0000
   9.000   1.6257   0.01798   0.01177  -0.1141   0.3238   1.0000
   9.250   1.6422   0.01885   0.01246  -0.1128   0.2747   1.0000
   9.500   1.6564   0.02008   0.01351  -0.1114   0.2312   1.0000
   9.750   1.6660   0.02180   0.01495  -0.1096   0.1844   1.0000
  10.000   1.6730   0.02366   0.01658  -0.1077   0.1447   1.0000
  10.250   1.6760   0.02572   0.01839  -0.1054   0.1083   1.0000
  10.500   1.6760   0.02783   0.02031  -0.1027   0.0769   1.0000
  10.750   1.6659   0.03025   0.02260  -0.0990   0.0511   1.0000
  11.000   1.6498   0.03348   0.02570  -0.0958   0.0313   1.0000
  11.250   1.6356   0.03721   0.02943  -0.0939   0.0222   1.0000
  11.500   1.6238   0.04118   0.03349  -0.0928   0.0189   1.0000
  11.750   1.6172   0.04481   0.03730  -0.0922   0.0173   1.0000
  12.000   1.6109   0.04854   0.04121  -0.0919   0.0162   1.0000
  12.250   1.6039   0.05250   0.04533  -0.0917   0.0152   1.0000
  12.500   1.5960   0.05666   0.04964  -0.0917   0.0145   1.0000
  12.750   1.5877   0.06098   0.05410  -0.0919   0.0140   1.0000
  13.000   1.5785   0.06550   0.05876  -0.0922   0.0136   1.0000
  13.250   1.5696   0.07003   0.06342  -0.0925   0.0133   1.0000
  13.500   1.5600   0.07474   0.06825  -0.0928   0.0129   1.0000
  13.750   1.5522   0.07930   0.07293  -0.0931   0.0126   1.0000
  14.000   1.5462   0.08357   0.07732  -0.0930   0.0124   1.0000
  14.250   1.5435   0.08730   0.08117  -0.0922   0.0121   1.0000
  14.500   1.5437   0.09072   0.08472  -0.0912   0.0120   1.0000
  14.750   1.5443   0.09435   0.08853  -0.0908   0.0119   1.0000
  15.000   1.5433   0.09843   0.09280  -0.0909   0.0119   1.0000
  15.250   1.5399   0.10299   0.09759  -0.0916   0.0118   1.0000
  15.500   1.5348   0.10799   0.10280  -0.0931   0.0116   1.0000
  15.750   1.5286   0.11329   0.10832  -0.0950   0.0114   1.0000
  16.000   1.5212   0.11896   0.11421  -0.0974   0.0113   1.0000
  16.250   1.5128   0.12493   0.12044  -0.1001   0.0110   1.0000
  16.500   1.5032   0.13135   0.12707  -0.1033   0.0110   1.0000
  16.750   1.4929   0.13810   0.13404  -0.1068   0.0109   1.0000
  17.000   1.4821   0.14525   0.14139  -0.1110   0.0108   1.0000
  17.250   1.4707   0.15279   0.14913  -0.1156   0.0108   1.0000
  17.500   1.4586   0.16077   0.15730  -0.1207   0.0108   1.0000
  17.750   1.4437   0.16976   0.16648  -0.1265   0.0113   1.0000
  18.000   1.4325   0.17840   0.17525  -0.1325   0.0111   1.0000
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