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EPPLER 397 AIRFOIL (e397-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 397 AIRFOIL (e397-il)
Reynolds number: 100,000
Max Cl/Cd: 50.95 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e397-il-100000.txt
Download as CSV file: xf-e397-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2679   0.10847   0.10419  -0.0605   0.9684   0.1247
  -8.500  -0.2682   0.10541   0.10115  -0.0636   0.9618   0.1304
  -8.250  -0.3559   0.08388   0.07982  -0.0786   0.9505   0.0657
  -8.000  -0.2953   0.09025   0.08605  -0.0738   0.9485   0.0873
  -7.750  -0.4173   0.06057   0.05621  -0.0998   0.9330   0.0556
  -7.500  -0.3957   0.05655   0.05203  -0.1049   0.9293   0.0578
  -7.250  -0.4021   0.05184   0.04697  -0.1069   0.9214   0.0588
  -7.000  -0.3814   0.04549   0.03985  -0.1136   0.9173   0.0621
  -6.750  -0.3466   0.04019   0.03373  -0.1196   0.9148   0.0681
  -6.500  -0.3323   0.03912   0.03246  -0.1188   0.9090   0.0745
  -6.250  -0.3036   0.03707   0.03012  -0.1207   0.9048   0.0832
  -6.000  -0.2676   0.03528   0.02799  -0.1235   0.9017   0.0952
  -5.750  -0.2276   0.03392   0.02637  -0.1266   0.8994   0.1094
  -5.500  -0.2142   0.03335   0.02548  -0.1250   0.8934   0.1194
  -5.250  -0.1841   0.03262   0.02463  -0.1261   0.8892   0.1340
  -5.000  -0.1481   0.03191   0.02393  -0.1282   0.8861   0.1512
  -4.750  -0.1155   0.03153   0.02351  -0.1296   0.8830   0.1696
  -4.500  -0.1015   0.03145   0.02338  -0.1280   0.8770   0.1837
  -4.250  -0.0696   0.03120   0.02302  -0.1292   0.8730   0.2062
  -4.000  -0.0326   0.03096   0.02282  -0.1312   0.8702   0.2304
  -3.750  -0.0141   0.03114   0.02297  -0.1303   0.8652   0.2501
  -3.500   0.0083   0.03124   0.02302  -0.1299   0.8601   0.2719
  -3.250   0.0419   0.03124   0.02305  -0.1312   0.8565   0.2982
  -3.000   0.0808   0.03122   0.02304  -0.1333   0.8540   0.3265
  -2.750   0.0858   0.03178   0.02361  -0.1304   0.8471   0.3423
  -2.500   0.1147   0.03192   0.02374  -0.1309   0.8428   0.3679
  -2.250   0.1516   0.03198   0.02377  -0.1327   0.8398   0.3970
  -2.000   0.1651   0.03251   0.02436  -0.1309   0.8342   0.4160
  -1.750   0.1865   0.03285   0.02474  -0.1304   0.8289   0.4389
  -1.500   0.2203   0.03298   0.02490  -0.1315   0.8255   0.4670
  -1.250   0.2499   0.03326   0.02520  -0.1321   0.8218   0.4944
  -1.000   0.2569   0.03397   0.02598  -0.1295   0.8147   0.5136
  -0.750   0.2882   0.03416   0.02622  -0.1302   0.8109   0.5434
  -0.500   0.3278   0.03418   0.02630  -0.1319   0.8083   0.5770
  -0.250   0.3249   0.03524   0.02743  -0.1281   0.7998   0.5968
   0.000   0.3549   0.03544   0.02772  -0.1284   0.7958   0.6316
   0.250   0.3935   0.03540   0.02777  -0.1296   0.7931   0.6720
   0.500   0.3888   0.03656   0.02904  -0.1256   0.7842   0.6993
   0.750   0.4173   0.03665   0.02925  -0.1253   0.7802   0.7464
   1.000   0.4391   0.03681   0.02957  -0.1238   0.7759   0.8013
   1.250   0.4334   0.03743   0.03041  -0.1186   0.7677   0.8758
   1.500   0.4783   0.03739   0.03027  -0.1220   0.7639   1.0000
   1.750   0.4908   0.03864   0.03140  -0.1214   0.7556   1.0000
   2.000   0.5246   0.03912   0.03175  -0.1230   0.7505   1.0000
   2.250   0.5703   0.03918   0.03169  -0.1256   0.7476   1.0000
   2.500   0.5694   0.04081   0.03327  -0.1231   0.7372   1.0000
   2.750   0.6109   0.04088   0.03328  -0.1250   0.7335   1.0000
   3.000   0.6166   0.04235   0.03472  -0.1231   0.7238   1.0000
   3.250   0.6538   0.04251   0.03483  -0.1245   0.7192   1.0000
   3.500   0.6976   0.04242   0.03472  -0.1264   0.7162   1.0000
   3.750   0.6985   0.04403   0.03632  -0.1240   0.7048   1.0000
   4.000   0.7447   0.04370   0.03598  -0.1260   0.7020   1.0000
   4.250   0.7452   0.04539   0.03769  -0.1235   0.6901   1.0000
   4.500   0.7917   0.04488   0.03719  -0.1254   0.6872   1.0000
   4.750   0.7939   0.04655   0.03888  -0.1231   0.6752   1.0000
   5.000   0.8406   0.04586   0.03823  -0.1248   0.6722   1.0000
   5.250   0.8444   0.04748   0.03989  -0.1227   0.6600   1.0000
   5.500   0.8921   0.04654   0.03901  -0.1243   0.6572   1.0000
   5.750   0.8969   0.04810   0.04061  -0.1222   0.6448   1.0000
   6.000   0.9465   0.04681   0.03941  -0.1237   0.6421   1.0000
   6.250   0.9526   0.04824   0.04090  -0.1217   0.6295   1.0000
   6.500   1.0045   0.04650   0.03926  -0.1231   0.6271   1.0000
   6.750   1.0129   0.04772   0.04057  -0.1212   0.6145   1.0000
   7.000   1.0337   0.04801   0.04094  -0.1202   0.6046   1.0000
   7.250   1.0777   0.04635   0.03942  -0.1206   0.5997   1.0000
   7.500   1.1362   0.04329   0.03653  -0.1218   0.5982   1.0000
   7.750   1.2079   0.03893   0.03236  -0.1239   0.5977   1.0000
   8.000   1.3162   0.03220   0.02587  -0.1303   0.5951   1.0000
   8.250   1.3497   0.03075   0.02456  -0.1296   0.5823   1.0000
   8.500   1.3732   0.03003   0.02395  -0.1279   0.5686   1.0000
   8.750   1.4006   0.02914   0.02318  -0.1267   0.5538   1.0000
   9.000   1.4317   0.02810   0.02223  -0.1259   0.5369   1.0000
   9.250   1.4397   0.02830   0.02253  -0.1225   0.5179   1.0000
   9.500   1.4486   0.02855   0.02284  -0.1193   0.4964   1.0000
   9.750   1.4612   0.02872   0.02302  -0.1165   0.4719   1.0000
  10.000   1.4699   0.02921   0.02345  -0.1135   0.4445   1.0000
  10.250   1.4731   0.03017   0.02433  -0.1101   0.4152   1.0000
  10.500   1.4734   0.03149   0.02553  -0.1067   0.3855   1.0000
  10.750   1.4712   0.03313   0.02705  -0.1033   0.3555   1.0000
  11.000   1.4664   0.03511   0.02890  -0.1000   0.3255   1.0000
  11.250   1.4593   0.03741   0.03106  -0.0968   0.2959   1.0000
  11.500   1.4505   0.04001   0.03352  -0.0939   0.2665   1.0000
  11.750   1.4404   0.04292   0.03627  -0.0912   0.2375   1.0000
  12.000   1.4294   0.04611   0.03929  -0.0888   0.2090   1.0000
  12.250   1.4183   0.04955   0.04256  -0.0866   0.1815   1.0000
  12.500   1.4088   0.05308   0.04590  -0.0848   0.1566   1.0000
  12.750   1.4022   0.05648   0.04911  -0.0832   0.1372   1.0000
  13.000   1.3996   0.05961   0.05206  -0.0819   0.1214   1.0000
  13.250   1.4000   0.06252   0.05488  -0.0807   0.1082   1.0000
  13.500   1.4009   0.06547   0.05786  -0.0798   0.0968   1.0000
  13.750   1.4034   0.06838   0.06083  -0.0788   0.0863   1.0000
  14.000   1.4064   0.07129   0.06377  -0.0779   0.0770   1.0000
  14.250   1.4109   0.07407   0.06649  -0.0771   0.0690   1.0000
  14.500   1.4131   0.07711   0.06959  -0.0766   0.0624   1.0000
  14.750   1.4209   0.07984   0.07240  -0.0758   0.0561   1.0000
  15.000   1.4416   0.08165   0.07404  -0.0746   0.0495   1.0000
  15.250   1.4409   0.08532   0.07807  -0.0742   0.0465   1.0000
  15.500   1.4445   0.08853   0.08139  -0.0739   0.0431   1.0000
  15.750   1.4643   0.09173   0.08469  -0.0730   0.0398   1.0000
  16.000   1.4551   0.09634   0.08968  -0.0731   0.0388   1.0000
  16.250   1.4450   0.10122   0.09490  -0.0737   0.0379   1.0000
  16.500   1.4341   0.10632   0.10030  -0.0747   0.0369   1.0000
  16.750   1.4229   0.11154   0.10579  -0.0760   0.0361   1.0000
  17.000   1.4127   0.11674   0.11122  -0.0777   0.0352   1.0000
  17.250   1.4092   0.12101   0.11559  -0.0791   0.0340   1.0000
  17.500   1.4009   0.12615   0.12088  -0.0811   0.0332   1.0000
  17.750   1.3878   0.13228   0.12722  -0.0839   0.0329   1.0000
  18.000   1.3610   0.14098   0.13628  -0.0890   0.0335   1.0000
  18.250   1.2960   0.15940   0.15529  -0.1016   0.0374   1.0000
  18.500   1.2691   0.17091   0.16696  -0.1096   0.0387   1.0000
  18.750   1.2471   0.18207   0.17821  -0.1172   0.0397   1.0000
  19.000   1.2316   0.19228   0.18845  -0.1237   0.0404   1.0000
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