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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 200,000
Max Cl/Cd: 86.42 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e393-il-200000-n5.txt
Download as CSV file: xf-e393-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 393 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.3318   0.09283   0.08945  -0.0453   1.0000   0.0144
  -9.000  -0.3363   0.08975   0.08643  -0.0452   1.0000   0.0141
  -8.750  -0.3382   0.08576   0.08250  -0.0468   0.9987   0.0139
  -8.500  -0.3285   0.07968   0.07644  -0.0532   0.9924   0.0136
  -8.250  -0.3210   0.07288   0.06966  -0.0607   0.9841   0.0134
  -7.750  -0.3248   0.04671   0.04327  -0.0933   0.9468   0.0122
  -7.500  -0.3183   0.03551   0.03129  -0.1040   0.9309   0.0121
  -7.250  -0.2975   0.03020   0.02535  -0.1078   0.9191   0.0122
  -7.000  -0.2708   0.02671   0.02131  -0.1104   0.9092   0.0126
  -6.750  -0.2403   0.02385   0.01794  -0.1126   0.9005   0.0132
  -6.500  -0.2106   0.02178   0.01546  -0.1138   0.8898   0.0141
  -6.250  -0.1797   0.02051   0.01379  -0.1148   0.8791   0.0154
  -6.000  -0.1504   0.01885   0.01192  -0.1159   0.8682   0.0167
  -5.750  -0.1206   0.01771   0.01060  -0.1166   0.8572   0.0177
  -5.500  -0.0919   0.01671   0.00943  -0.1170   0.8456   0.0190
  -5.250  -0.0640   0.01583   0.00837  -0.1171   0.8337   0.0207
  -5.000  -0.0363   0.01502   0.00737  -0.1173   0.8224   0.0227
  -4.750  -0.0086   0.01444   0.00671  -0.1175   0.8116   0.0271
  -4.500   0.0195   0.01391   0.00604  -0.1177   0.8015   0.0322
  -4.250   0.0470   0.01349   0.00553  -0.1178   0.7910   0.0399
  -4.000   0.0748   0.01304   0.00501  -0.1179   0.7813   0.0507
  -3.750   0.1028   0.01262   0.00457  -0.1181   0.7724   0.0710
  -3.500   0.1305   0.01226   0.00424  -0.1183   0.7631   0.1007
  -3.250   0.1582   0.01190   0.00397  -0.1186   0.7547   0.1470
  -3.000   0.1859   0.01148   0.00374  -0.1189   0.7466   0.2203
  -2.750   0.2134   0.01102   0.00359  -0.1193   0.7386   0.3230
  -2.500   0.2410   0.01078   0.00353  -0.1194   0.7313   0.4068
  -2.250   0.2685   0.01068   0.00349  -0.1194   0.7237   0.4589
  -2.000   0.2963   0.01064   0.00345  -0.1193   0.7170   0.5000
  -1.750   0.3238   0.01061   0.00342  -0.1192   0.7098   0.5335
  -1.500   0.3515   0.01062   0.00339  -0.1191   0.7034   0.5610
  -1.250   0.3790   0.01062   0.00338  -0.1190   0.6967   0.5858
  -1.000   0.4065   0.01062   0.00337  -0.1188   0.6904   0.6090
  -0.750   0.4339   0.01064   0.00338  -0.1187   0.6845   0.6306
  -0.500   0.4611   0.01065   0.00339  -0.1185   0.6782   0.6518
  -0.250   0.4884   0.01068   0.00341  -0.1183   0.6728   0.6731
   0.000   0.5152   0.01068   0.00345  -0.1180   0.6665   0.6940
   0.250   0.5422   0.01071   0.00348  -0.1177   0.6610   0.7152
   0.500   0.5685   0.01073   0.00354  -0.1173   0.6553   0.7359
   0.750   0.5948   0.01076   0.00360  -0.1169   0.6495   0.7577
   1.000   0.6207   0.01080   0.00365  -0.1164   0.6447   0.7804
   1.250   0.6456   0.01081   0.00374  -0.1157   0.6385   0.8060
   1.500   0.6699   0.01083   0.00381  -0.1148   0.6332   0.8354
   1.750   0.6933   0.01084   0.00386  -0.1136   0.6280   0.8710
   2.000   0.7169   0.01080   0.00390  -0.1125   0.6221   0.9205
   2.250   0.7490   0.01083   0.00390  -0.1134   0.6170   1.0000
   2.500   0.7772   0.01096   0.00405  -0.1137   0.6109   1.0000
   2.750   0.8054   0.01111   0.00417  -0.1139   0.6051   1.0000
   3.000   0.8334   0.01126   0.00430  -0.1140   0.5994   1.0000
   3.250   0.8609   0.01140   0.00446  -0.1141   0.5926   1.0000
   3.500   0.8885   0.01156   0.00461  -0.1141   0.5859   1.0000
   3.750   0.9155   0.01170   0.00478  -0.1141   0.5777   1.0000
   4.000   0.9425   0.01185   0.00494  -0.1140   0.5701   1.0000
   4.250   0.9692   0.01200   0.00511  -0.1139   0.5616   1.0000
   4.500   0.9956   0.01216   0.00532  -0.1137   0.5523   1.0000
   4.750   1.0219   0.01232   0.00550  -0.1134   0.5431   1.0000
   5.000   1.0478   0.01249   0.00570  -0.1131   0.5328   1.0000
   5.250   1.0733   0.01267   0.00592  -0.1127   0.5210   1.0000
   5.500   1.0985   0.01286   0.00617  -0.1123   0.5086   1.0000
   5.750   1.1234   0.01306   0.00641  -0.1118   0.4954   1.0000
   6.000   1.1477   0.01329   0.00667  -0.1112   0.4803   1.0000
   6.250   1.1710   0.01355   0.00694  -0.1105   0.4621   1.0000
   6.500   1.1938   0.01385   0.00725  -0.1096   0.4411   1.0000
   6.750   1.2152   0.01422   0.00761  -0.1086   0.4170   1.0000
   7.000   1.2349   0.01468   0.00801  -0.1073   0.3857   1.0000
   7.250   1.2515   0.01532   0.00851  -0.1055   0.3460   1.0000
   7.500   1.2644   0.01619   0.00916  -0.1033   0.2994   1.0000
   7.750   1.2757   0.01719   0.00995  -0.1009   0.2565   1.0000
   8.000   1.2861   0.01823   0.01081  -0.0984   0.2184   1.0000
   8.250   1.2963   0.01925   0.01169  -0.0959   0.1860   1.0000
   8.500   1.3044   0.02024   0.01261  -0.0931   0.1592   1.0000
   8.750   1.3106   0.02136   0.01360  -0.0901   0.1324   1.0000
   9.000   1.3149   0.02263   0.01472  -0.0871   0.1057   1.0000
   9.250   1.3182   0.02403   0.01595  -0.0842   0.0806   1.0000
   9.500   1.3221   0.02545   0.01726  -0.0815   0.0615   1.0000
   9.750   1.3281   0.02681   0.01859  -0.0793   0.0485   1.0000
  10.000   1.3343   0.02823   0.02002  -0.0772   0.0389   1.0000
  10.250   1.3395   0.02980   0.02160  -0.0753   0.0306   1.0000
  10.500   1.3433   0.03157   0.02338  -0.0734   0.0233   1.0000
  10.750   1.3474   0.03342   0.02533  -0.0717   0.0182   1.0000
  11.000   1.3496   0.03554   0.02752  -0.0700   0.0151   1.0000
  11.250   1.3532   0.03762   0.02972  -0.0686   0.0131   1.0000
  11.500   1.3545   0.04000   0.03218  -0.0674   0.0117   1.0000
  11.750   1.3570   0.04235   0.03465  -0.0663   0.0107   1.0000
  12.000   1.3606   0.04465   0.03708  -0.0655   0.0098   1.0000
  12.250   1.3635   0.04709   0.03964  -0.0648   0.0090   1.0000
  12.500   1.3644   0.04980   0.04247  -0.0642   0.0085   1.0000
  12.750   1.3630   0.05289   0.04569  -0.0638   0.0082   1.0000
  13.000   1.3597   0.05630   0.04923  -0.0634   0.0079   1.0000
  13.250   1.3592   0.05948   0.05257  -0.0633   0.0077   1.0000
  13.500   1.3581   0.06283   0.05608  -0.0633   0.0075   1.0000
  13.750   1.3565   0.06635   0.05975  -0.0634   0.0073   1.0000
  14.000   1.3545   0.07003   0.06359  -0.0637   0.0072   1.0000
  14.250   1.3524   0.07383   0.06759  -0.0642   0.0070   1.0000
  14.500   1.3501   0.07776   0.07167  -0.0648   0.0069   1.0000
  14.750   1.3474   0.08185   0.07591  -0.0655   0.0067   1.0000
  15.000   1.3445   0.08608   0.08030  -0.0664   0.0066   1.0000
  15.250   1.3414   0.09043   0.08482  -0.0675   0.0065   1.0000
  15.500   1.3377   0.09498   0.08954  -0.0688   0.0064   1.0000
  15.750   1.3336   0.09971   0.09443  -0.0703   0.0063   1.0000
  16.000   1.3289   0.10463   0.09952  -0.0720   0.0062   1.0000
  16.250   1.3238   0.10976   0.10483  -0.0740   0.0062   1.0000
  16.500   1.3178   0.11518   0.11043  -0.0763   0.0061   1.0000
  16.750   1.3111   0.12087   0.11629  -0.0789   0.0061   1.0000
  17.000   1.3036   0.12685   0.12246  -0.0819   0.0060   1.0000
  17.250   1.2955   0.13314   0.12894  -0.0852   0.0060   1.0000
  17.500   1.2867   0.13981   0.13579  -0.0890   0.0060   1.0000
  17.750   1.2769   0.14691   0.14307  -0.0933   0.0060   1.0000
  18.000   1.2661   0.15452   0.15087  -0.0981   0.0060   1.0000
  18.250   1.2540   0.16274   0.15928  -0.1034   0.0060   1.0000
  18.500   1.2404   0.17185   0.16858  -0.1094   0.0060   1.0000
  18.750   1.2249   0.18206   0.17897  -0.1162   0.0061   1.0000
  19.000   1.2040   0.19491   0.19201  -0.1247   0.0063   1.0000
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