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EPPLER 398 AIRFOIL (e398-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 398 AIRFOIL (e398-il)
Reynolds number: 100,000
Max Cl/Cd: 47.52 at α=10.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e398-il-100000.txt
Download as CSV file: xf-e398-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 398 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2291   0.10400   0.09975  -0.0640   0.9660   0.1303
  -8.500  -0.2999   0.08289   0.07876  -0.0827   0.9528   0.0704
  -8.250  -0.3657   0.06363   0.05934  -0.1024   0.9353   0.0598
  -8.000  -0.3674   0.05601   0.05143  -0.1104   0.9263   0.0592
  -7.750  -0.3658   0.04881   0.04364  -0.1169   0.9170   0.0590
  -7.500  -0.3553   0.04293   0.03690  -0.1213   0.9088   0.0602
  -7.250  -0.3278   0.04180   0.03599  -0.1224   0.9031   0.0662
  -7.000  -0.2919   0.03711   0.03053  -0.1279   0.8996   0.0735
  -6.750  -0.2744   0.03601   0.02917  -0.1274   0.8910   0.0809
  -6.500  -0.2397   0.03416   0.02713  -0.1300   0.8864   0.0916
  -6.250  -0.1973   0.03235   0.02503  -0.1336   0.8837   0.1054
  -6.000  -0.1825   0.03157   0.02411  -0.1323   0.8752   0.1143
  -5.750  -0.1461   0.03041   0.02277  -0.1344   0.8708   0.1287
  -5.500  -0.1021   0.02927   0.02149  -0.1377   0.8682   0.1465
  -5.250  -0.0875   0.02897   0.02110  -0.1360   0.8598   0.1584
  -5.000  -0.0527   0.02834   0.02041  -0.1376   0.8554   0.1775
  -4.750  -0.0086   0.02752   0.01946  -0.1407   0.8529   0.2022
  -4.500   0.0068   0.02762   0.01956  -0.1391   0.8449   0.2186
  -4.250   0.0389   0.02734   0.01930  -0.1401   0.8401   0.2415
  -4.000   0.0812   0.02684   0.01879  -0.1427   0.8375   0.2694
  -3.750   0.1263   0.02635   0.01825  -0.1457   0.8356   0.2996
  -3.500   0.1262   0.02708   0.01895  -0.1416   0.8248   0.3137
  -3.250   0.1671   0.02674   0.01863  -0.1438   0.8220   0.3424
  -3.000   0.2096   0.02633   0.01825  -0.1461   0.8199   0.3712
  -2.750   0.2072   0.02730   0.01924  -0.1419   0.8095   0.3846
  -2.500   0.2465   0.02703   0.01894  -0.1437   0.8064   0.4138
  -2.250   0.2891   0.02664   0.01852  -0.1459   0.8043   0.4443
  -2.000   0.2842   0.02783   0.01980  -0.1415   0.7941   0.4569
  -1.750   0.3208   0.02764   0.01965  -0.1427   0.7908   0.4848
  -1.500   0.3623   0.02725   0.01927  -0.1446   0.7886   0.5151
  -1.250   0.3552   0.02867   0.02072  -0.1400   0.7783   0.5297
  -1.000   0.3913   0.02853   0.02061  -0.1412   0.7751   0.5603
  -0.750   0.4315   0.02815   0.02028  -0.1426   0.7729   0.5920
  -0.500   0.4189   0.02984   0.02205  -0.1374   0.7621   0.6074
  -0.250   0.4546   0.02966   0.02194  -0.1382   0.7591   0.6410
   0.000   0.4941   0.02925   0.02160  -0.1394   0.7570   0.6774
   0.250   0.4742   0.03130   0.02377  -0.1333   0.7455   0.6962
   0.500   0.5086   0.03101   0.02355  -0.1335   0.7428   0.7385
   0.750   0.5452   0.03047   0.02311  -0.1337   0.7409   0.7858
   1.000   0.5162   0.03287   0.02566  -0.1264   0.7287   0.8196
   1.250   0.5381   0.03221   0.02517  -0.1237   0.7261   0.9070
   1.500   0.5989   0.03152   0.02433  -0.1294   0.7246   1.0000
   1.750   0.5828   0.03445   0.02718  -0.1259   0.7120   1.0000
   2.000   0.6304   0.03409   0.02668  -0.1288   0.7100   1.0000
   2.250   0.6809   0.03352   0.02600  -0.1317   0.7086   1.0000
   2.500   0.6569   0.03681   0.02926  -0.1270   0.6954   1.0000
   2.750   0.6768   0.03785   0.03024  -0.1266   0.6895   1.0000
   3.000   0.6859   0.03938   0.03175  -0.1253   0.6812   1.0000
   3.250   0.7288   0.03905   0.03136  -0.1269   0.6787   1.0000
   3.500   0.7774   0.03831   0.03058  -0.1291   0.6772   1.0000
   3.750   0.7556   0.04173   0.03401  -0.1249   0.6640   1.0000
   4.000   0.7559   0.04391   0.03619  -0.1229   0.6544   1.0000
   4.250   0.7855   0.04426   0.03653  -0.1232   0.6493   1.0000
   4.500   0.8298   0.04365   0.03592  -0.1245   0.6469   1.0000
   4.750   0.8762   0.04284   0.03513  -0.1260   0.6450   1.0000
   5.000   0.8599   0.04609   0.03840  -0.1227   0.6318   1.0000
   5.250   0.8529   0.04884   0.04117  -0.1202   0.6200   1.0000
   5.500   0.8929   0.04832   0.04068  -0.1210   0.6166   1.0000
   5.750   0.9424   0.04705   0.03947  -0.1223   0.6149   1.0000
   6.000   0.9279   0.05038   0.04283  -0.1194   0.6014   1.0000
   6.250   0.9291   0.05264   0.04512  -0.1177   0.5904   1.0000
   6.500   0.9666   0.05205   0.04459  -0.1180   0.5861   1.0000
   6.750   1.0166   0.05036   0.04299  -0.1189   0.5841   1.0000
   7.000   1.0715   0.04807   0.04080  -0.1200   0.5831   1.0000
   7.250   1.1328   0.04511   0.03797  -0.1215   0.5826   1.0000
   7.500   1.1045   0.04962   0.04252  -0.1176   0.5659   1.0000
   7.750   1.1719   0.04581   0.03886  -0.1192   0.5663   1.0000
   8.000   1.2561   0.04123   0.03444  -0.1229   0.5668   1.0000
   8.250   1.2383   0.04397   0.03724  -0.1184   0.5530   1.0000
   8.500   1.3386   0.03834   0.03181  -0.1239   0.5525   1.0000
   8.750   1.3178   0.04080   0.03435  -0.1184   0.5390   1.0000
   9.000   1.4557   0.03357   0.02730  -0.1291   0.5361   1.0000
   9.250   1.4410   0.03491   0.02876  -0.1231   0.5234   1.0000
   9.500   1.4526   0.03491   0.02887  -0.1202   0.5113   1.0000
   9.750   1.4881   0.03350   0.02758  -0.1199   0.4988   1.0000
  10.000   1.5152   0.03253   0.02669  -0.1187   0.4846   1.0000
  10.250   1.5302   0.03222   0.02645  -0.1162   0.4691   1.0000
  10.500   1.5379   0.03236   0.02666  -0.1129   0.4523   1.0000
  10.750   1.5444   0.03266   0.02700  -0.1097   0.4338   1.0000
  11.000   1.5543   0.03286   0.02716  -0.1070   0.4130   1.0000
  11.250   1.5457   0.03446   0.02882  -0.1030   0.3924   1.0000
  11.500   1.5453   0.03568   0.02997  -0.0998   0.3690   1.0000
  11.750   1.5374   0.03772   0.03198  -0.0966   0.3453   1.0000
  12.000   1.5321   0.03974   0.03387  -0.0938   0.3206   1.0000
  12.250   1.5223   0.04237   0.03643  -0.0911   0.2961   1.0000
  12.500   1.5130   0.04518   0.03912  -0.0887   0.2721   1.0000
  12.750   1.5030   0.04824   0.04204  -0.0866   0.2490   1.0000
  13.000   1.4927   0.05157   0.04526  -0.0849   0.2269   1.0000
  13.250   1.4827   0.05505   0.04865  -0.0834   0.2061   1.0000
  13.500   1.4738   0.05859   0.05201  -0.0821   0.1868   1.0000
  13.750   1.4651   0.06235   0.05573  -0.0812   0.1682   1.0000
  14.000   1.4575   0.06611   0.05941  -0.0804   0.1513   1.0000
  14.250   1.4512   0.06985   0.06306  -0.0798   0.1360   1.0000
  14.500   1.4464   0.07353   0.06667  -0.0793   0.1221   1.0000
  14.750   1.4435   0.07707   0.07015  -0.0788   0.1095   1.0000
  15.000   1.4418   0.08053   0.07358  -0.0784   0.0985   1.0000
  15.250   1.4430   0.08369   0.07669  -0.0780   0.0888   1.0000
  15.500   1.4475   0.08638   0.07922  -0.0775   0.0798   1.0000
  15.750   1.4453   0.09022   0.08332  -0.0777   0.0734   1.0000
  16.000   1.4512   0.09288   0.08592  -0.0773   0.0668   1.0000
  16.250   1.4518   0.09635   0.08953  -0.0775   0.0617   1.0000
  16.500   1.4596   0.09891   0.09208  -0.0771   0.0565   1.0000
  16.750   1.4585   0.10273   0.09613  -0.0776   0.0529   1.0000
  17.000   1.4722   0.10455   0.09781  -0.0770   0.0484   1.0000
  17.250   1.4643   0.10939   0.10301  -0.0782   0.0464   1.0000
  17.500   1.4608   0.11366   0.10749  -0.0792   0.0441   1.0000
  17.750   1.4696   0.11609   0.10990  -0.0793   0.0416   1.0000
  18.000   1.4668   0.12064   0.11467  -0.0804   0.0401   1.0000
  18.250   1.4525   0.12671   0.12109  -0.0829   0.0394   1.0000
  18.500   1.4364   0.13325   0.12794  -0.0860   0.0388   1.0000
  18.750   1.4199   0.14015   0.13513  -0.0897   0.0383   1.0000
  19.000   1.4014   0.14773   0.14298  -0.0940   0.0381   1.0000
  19.250   1.3799   0.15627   0.15178  -0.0994   0.0382   1.0000
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