Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 50,000
Max Cl/Cd: 22.5 at α=11.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e397-il-50000-n5.txt
Download as CSV file: xf-e397-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 397 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.250  -0.3238   0.13373   0.12713  -0.0470   1.0000   0.0512
 -11.000  -0.3329   0.13167   0.12516  -0.0456   1.0000   0.0510
 -10.750  -0.3428   0.12955   0.12314  -0.0442   1.0000   0.0513
 -10.500  -0.3388   0.12512   0.11873  -0.0473   0.9964   0.0519
 -10.250  -0.3341   0.11969   0.11332  -0.0521   0.9913   0.0530
 -10.000  -0.3299   0.11426   0.10791  -0.0566   0.9858   0.0534
  -9.750  -0.3280   0.10850   0.10218  -0.0613   0.9803   0.0539
  -9.500  -0.3287   0.10259   0.09630  -0.0657   0.9739   0.0541
  -9.250  -0.3087   0.10117   0.09485  -0.0669   0.9692   0.0571
  -9.000  -0.3053   0.09730   0.09100  -0.0696   0.9621   0.0595
  -8.750  -0.3060   0.09197   0.08571  -0.0740   0.9559   0.0608
  -8.500  -0.3146   0.08657   0.08037  -0.0775   0.9474   0.0614
  -8.250  -0.3286   0.08067   0.07453  -0.0813   0.9387   0.0617
  -8.000  -0.3459   0.07196   0.06583  -0.0892   0.9299   0.0612
  -7.750  -0.3693   0.06243   0.05612  -0.0989   0.9182   0.0603
  -7.500  -0.3760   0.05484   0.04807  -0.1062   0.9099   0.0614
  -7.250  -0.3677   0.04786   0.04016  -0.1128   0.9031   0.0651
  -7.000  -0.3398   0.04632   0.03863  -0.1149   0.8997   0.0713
  -6.750  -0.3257   0.04284   0.03446  -0.1166   0.8929   0.0778
  -6.500  -0.3006   0.04160   0.03318  -0.1177   0.8884   0.0855
  -6.250  -0.2688   0.03967   0.03092  -0.1203   0.8852   0.0959
  -6.000  -0.2474   0.03817   0.02905  -0.1208   0.8798   0.1062
  -5.750  -0.2218   0.03700   0.02756  -0.1217   0.8749   0.1181
  -5.500  -0.1906   0.03600   0.02639  -0.1232   0.8714   0.1323
  -5.250  -0.1569   0.03511   0.02534  -0.1251   0.8685   0.1486
  -5.000  -0.1409   0.03475   0.02486  -0.1240   0.8619   0.1616
  -4.750  -0.1118   0.03420   0.02421  -0.1249   0.8578   0.1794
  -4.500  -0.0786   0.03375   0.02369  -0.1264   0.8548   0.1996
  -4.250  -0.0578   0.03358   0.02343  -0.1259   0.8494   0.2176
  -4.000  -0.0328   0.03337   0.02304  -0.1261   0.8445   0.2387
  -3.750  -0.0022   0.03318   0.02283  -0.1269   0.8410   0.2609
  -3.500   0.0331   0.03292   0.02242  -0.1286   0.8384   0.2870
  -3.250   0.0455   0.03319   0.02266  -0.1267   0.8313   0.3042
  -3.000   0.0738   0.03316   0.02256  -0.1271   0.8272   0.3276
  -2.750   0.1070   0.03306   0.02237  -0.1283   0.8242   0.3530
  -2.500   0.1244   0.03337   0.02264  -0.1271   0.8183   0.3733
  -2.250   0.1496   0.03352   0.02269  -0.1271   0.8135   0.3974
  -2.000   0.1804   0.03354   0.02267  -0.1277   0.8101   0.4223
  -1.750   0.2067   0.03371   0.02280  -0.1278   0.8060   0.4470
  -1.500   0.2232   0.03414   0.02321  -0.1265   0.7997   0.4683
  -1.250   0.2523   0.03425   0.02329  -0.1269   0.7959   0.4952
  -1.000   0.2853   0.03426   0.02328  -0.1277   0.7931   0.5247
  -0.750   0.2949   0.03494   0.02400  -0.1254   0.7857   0.5460
  -0.500   0.3212   0.03513   0.02421  -0.1253   0.7814   0.5755
  -0.250   0.3518   0.03518   0.02429  -0.1256   0.7784   0.6083
   0.000   0.3621   0.03588   0.02505  -0.1234   0.7712   0.6361
   0.250   0.3846   0.03610   0.02534  -0.1225   0.7665   0.6711
   0.500   0.4122   0.03612   0.02543  -0.1221   0.7633   0.7132
   0.750   0.4176   0.03680   0.02624  -0.1189   0.7558   0.7523
   1.000   0.4347   0.03688   0.02643  -0.1167   0.7509   0.8111
   1.250   0.4612   0.03652   0.02619  -0.1159   0.7474   1.0000
   1.500   0.4738   0.03770   0.02721  -0.1153   0.7388   1.0000
   1.750   0.5070   0.03815   0.02749  -0.1169   0.7347   1.0000
   2.000   0.5443   0.03844   0.02762  -0.1187   0.7318   1.0000
   2.250   0.5513   0.03977   0.02888  -0.1171   0.7222   1.0000
   2.500   0.5844   0.04015   0.02917  -0.1182   0.7185   1.0000
   2.750   0.5981   0.04126   0.03023  -0.1173   0.7105   1.0000
   3.000   0.6249   0.04186   0.03076  -0.1176   0.7052   1.0000
   3.250   0.6603   0.04208   0.03093  -0.1188   0.7019   1.0000
   3.500   0.6665   0.04352   0.03236  -0.1170   0.6918   1.0000
   3.750   0.6995   0.04381   0.03264  -0.1179   0.6878   1.0000
   4.000   0.7090   0.04515   0.03398  -0.1164   0.6784   1.0000
   4.250   0.7394   0.04550   0.03433  -0.1169   0.6735   1.0000
   4.500   0.7520   0.04672   0.03559  -0.1158   0.6646   1.0000
   4.750   0.7799   0.04716   0.03605  -0.1160   0.6589   1.0000
   5.250   0.8211   0.04872   0.03770  -0.1150   0.6439   1.0000
   5.750   0.8631   0.05016   0.03929  -0.1139   0.6285   1.0000
   6.000   0.8747   0.05144   0.04064  -0.1127   0.6182   1.0000
   6.250   0.9065   0.05141   0.04072  -0.1128   0.6127   1.0000
   6.500   0.9157   0.05281   0.04221  -0.1114   0.6013   1.0000
   6.750   0.9515   0.05239   0.04191  -0.1117   0.5967   1.0000
   7.000   0.9593   0.05387   0.04349  -0.1102   0.5844   1.0000
   7.500   1.0060   0.05445   0.04435  -0.1088   0.5674   1.0000
   7.750   1.0160   0.05573   0.04576  -0.1074   0.5548   1.0000
   8.250   1.0657   0.05562   0.04597  -0.1058   0.5371   1.0000
   8.500   1.0768   0.05672   0.04722  -0.1043   0.5239   1.0000
   8.750   1.0903   0.05759   0.04825  -0.1030   0.5112   1.0000
   9.250   1.1432   0.05645   0.04751  -0.1008   0.4921   1.0000
   9.500   1.1572   0.05714   0.04836  -0.0993   0.4783   1.0000
   9.750   1.1735   0.05752   0.04893  -0.0979   0.4644   1.0000
  10.000   1.1916   0.05768   0.04928  -0.0965   0.4502   1.0000
  10.250   1.2113   0.05760   0.04939  -0.0950   0.4353   1.0000
  10.500   1.2337   0.05708   0.04904  -0.0934   0.4189   1.0000
  10.750   1.2589   0.05616   0.04822  -0.0917   0.4002   1.0000
  11.000   1.2664   0.05749   0.04969  -0.0901   0.3785   1.0000
  11.250   1.2864   0.05717   0.04937  -0.0883   0.3547   1.0000
  11.500   1.2928   0.05868   0.05090  -0.0867   0.3298   1.0000
  11.750   1.2991   0.06021   0.05240  -0.0852   0.3044   1.0000
  12.000   1.3048   0.06189   0.05398  -0.0837   0.2803   1.0000
  12.250   1.3057   0.06445   0.05659  -0.0825   0.2584   1.0000
  12.500   1.3078   0.06689   0.05903  -0.0814   0.2380   1.0000
  12.750   1.3073   0.06977   0.06189  -0.0805   0.2178   1.0000
  13.000   1.3052   0.07296   0.06509  -0.0798   0.1978   1.0000
  13.250   1.3023   0.07633   0.06839  -0.0793   0.1793   1.0000
  13.500   1.2992   0.07987   0.07189  -0.0789   0.1621   1.0000
  13.750   1.2960   0.08358   0.07560  -0.0787   0.1457   1.0000
  14.000   1.2928   0.08738   0.07938  -0.0786   0.1313   1.0000
  14.250   1.2901   0.09121   0.08318  -0.0788   0.1188   1.0000
  14.500   1.2878   0.09497   0.08687  -0.0790   0.1084   1.0000
  14.750   1.2868   0.09879   0.09083  -0.0794   0.0984   1.0000
  15.000   1.2864   0.10254   0.09465  -0.0799   0.0901   1.0000
  15.250   1.2864   0.10612   0.09823  -0.0804   0.0832   1.0000
  15.500   1.2866   0.11002   0.10236  -0.0811   0.0763   1.0000
  15.750   1.2877   0.11344   0.10573  -0.0818   0.0709   1.0000
  16.000   1.2874   0.11763   0.11021  -0.0828   0.0656   1.0000
  16.250   1.2880   0.12125   0.11385  -0.0839   0.0612   1.0000
  16.500   1.2883   0.12533   0.11811  -0.0850   0.0574   1.0000
  16.750   1.2866   0.12981   0.12280  -0.0867   0.0540   1.0000
  17.000   1.2907   0.13274   0.12566  -0.0876   0.0506   1.0000
  17.250   1.2867   0.13794   0.13112  -0.0898   0.0484   1.0000
  17.500   1.2780   0.14434   0.13785  -0.0930   0.0468   1.0000
  17.750   1.2681   0.15115   0.14492  -0.0969   0.0454   1.0000
  18.000   1.2570   0.15849   0.15248  -0.1013   0.0443   1.0000
  18.250   1.2423   0.16717   0.16138  -0.1068   0.0437   1.0000
  18.500   1.2111   0.18202   0.17647  -0.1167   0.0449   1.0000
<< Back to EPPLER 397 AIRFOIL (e397-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 397 AIRFOIL (e397-il)