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EPPLER 399 AIRFOIL (e399-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 399 AIRFOIL (e399-il)
Reynolds number: 50,000
Max Cl/Cd: 16.93 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e399-il-50000-n5.txt
Download as CSV file: xf-e399-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 399 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.3086   0.12540   0.11867  -0.0544   1.0000   0.0554
 -11.250  -0.3201   0.12208   0.11547  -0.0540   1.0000   0.0559
 -11.000  -0.3328   0.11897   0.11248  -0.0533   1.0000   0.0562
 -10.750  -0.3361   0.11817   0.11177  -0.0508   1.0000   0.0577
 -10.500  -0.3457   0.11648   0.11018  -0.0488   1.0000   0.0586
 -10.250  -0.3468   0.11275   0.10650  -0.0505   0.9971   0.0597
 -10.000  -0.3408   0.10702   0.10078  -0.0557   0.9908   0.0616
  -9.750  -0.3409   0.10027   0.09406  -0.0617   0.9838   0.0632
  -9.500  -0.3507   0.09206   0.08590  -0.0683   0.9751   0.0641
  -9.250  -0.3696   0.08226   0.07616  -0.0761   0.9654   0.0645
  -9.000  -0.3943   0.07287   0.06676  -0.0843   0.9535   0.0641
  -8.750  -0.4222   0.06381   0.05753  -0.0940   0.9389   0.0634
  -8.500  -0.4365   0.05544   0.04867  -0.1035   0.9263   0.0640
  -8.250  -0.4288   0.05174   0.04474  -0.1065   0.9165   0.0672
  -8.000  -0.4146   0.04850   0.04117  -0.1094   0.9086   0.0722
  -7.750  -0.3974   0.04540   0.03771  -0.1119   0.9008   0.0777
  -7.500  -0.3716   0.04228   0.03402  -0.1155   0.8953   0.0860
  -7.250  -0.3533   0.04133   0.03312  -0.1153   0.8869   0.0929
  -7.000  -0.3226   0.03934   0.03084  -0.1179   0.8822   0.1031
  -6.750  -0.3006   0.03775   0.02892  -0.1187   0.8750   0.1132
  -6.500  -0.2731   0.03648   0.02739  -0.1200   0.8689   0.1252
  -6.250  -0.2380   0.03525   0.02597  -0.1224   0.8650   0.1398
  -6.000  -0.2188   0.03469   0.02540  -0.1218   0.8572   0.1517
  -5.750  -0.1888   0.03385   0.02441  -0.1231   0.8518   0.1679
  -5.500  -0.1522   0.03295   0.02330  -0.1254   0.8483   0.1876
  -5.250  -0.1335   0.03264   0.02290  -0.1246   0.8403   0.2032
  -5.000  -0.1036   0.03223   0.02246  -0.1255   0.8352   0.2221
  -4.750  -0.0675   0.03178   0.02192  -0.1273   0.8317   0.2443
  -4.500  -0.0498   0.03176   0.02183  -0.1262   0.8239   0.2616
  -4.250  -0.0196   0.03149   0.02139  -0.1270   0.8188   0.2844
  -4.000   0.0156   0.03123   0.02107  -0.1284   0.8153   0.3066
  -3.750   0.0323   0.03138   0.02117  -0.1270   0.8078   0.3241
  -3.500   0.0598   0.03133   0.02104  -0.1272   0.8025   0.3449
  -3.250   0.0952   0.03113   0.02067  -0.1287   0.7990   0.3688
  -3.000   0.1132   0.03137   0.02084  -0.1275   0.7920   0.3869
  -2.750   0.1382   0.03146   0.02088  -0.1273   0.7864   0.4062
  -2.500   0.1710   0.03136   0.02072  -0.1281   0.7829   0.4272
  -2.250   0.1914   0.03163   0.02094  -0.1272   0.7767   0.4454
  -2.000   0.2125   0.03188   0.02114  -0.1264   0.7705   0.4637
  -1.750   0.2445   0.03186   0.02104  -0.1271   0.7668   0.4851
  -1.500   0.2807   0.03173   0.02081  -0.1284   0.7641   0.5085
  -1.250   0.2842   0.03256   0.02167  -0.1252   0.7546   0.5223
  -1.000   0.3154   0.03258   0.02163  -0.1258   0.7507   0.5447
  -0.750   0.3492   0.03250   0.02153  -0.1265   0.7480   0.5666
  -0.500   0.3520   0.03346   0.02251  -0.1234   0.7387   0.5825
  -0.250   0.3803   0.03355   0.02259  -0.1234   0.7346   0.6053
   0.000   0.4141   0.03349   0.02251  -0.1242   0.7318   0.6311
   0.250   0.4149   0.03458   0.02367  -0.1208   0.7225   0.6491
   0.500   0.4402   0.03472   0.02384  -0.1202   0.7183   0.6744
   0.750   0.4712   0.03462   0.02376  -0.1203   0.7155   0.7035
   1.000   0.4696   0.03590   0.02513  -0.1167   0.7060   0.7269
   1.250   0.4918   0.03602   0.02531  -0.1155   0.7017   0.7598
   1.500   0.5184   0.03581   0.02517  -0.1146   0.6989   0.8002
   1.750   0.5106   0.03723   0.02672  -0.1102   0.6888   0.8435
   2.000   0.5360   0.03704   0.02661  -0.1096   0.6845   1.0000
   2.250   0.5782   0.03710   0.02649  -0.1124   0.6821   1.0000
   2.500   0.5798   0.03914   0.02847  -0.1110   0.6713   1.0000
   2.750   0.6138   0.03945   0.02865  -0.1124   0.6677   1.0000
   3.000   0.6416   0.04006   0.02917  -0.1130   0.6632   1.0000
   3.250   0.6487   0.04178   0.03087  -0.1119   0.6540   1.0000
   3.500   0.6826   0.04199   0.03100  -0.1129   0.6506   1.0000
   4.000   0.7136   0.04450   0.03346  -0.1117   0.6361   1.0000
   4.250   0.7487   0.04456   0.03350  -0.1126   0.6332   1.0000
   4.500   0.7462   0.04693   0.03589  -0.1107   0.6221   1.0000
   4.750   0.7774   0.04719   0.03615  -0.1111   0.6182   1.0000
   5.250   0.8069   0.04982   0.03882  -0.1097   0.6033   1.0000
   5.500   0.8421   0.04974   0.03878  -0.1103   0.6003   1.0000
   5.750   0.8376   0.05238   0.04145  -0.1084   0.5883   1.0000
   6.000   0.8707   0.05238   0.04151  -0.1088   0.5847   1.0000
   6.250   0.8688   0.05490   0.04409  -0.1071   0.5733   1.0000
   6.500   0.9000   0.05498   0.04423  -0.1073   0.5691   1.0000
   7.000   0.9305   0.05746   0.04688  -0.1058   0.5532   1.0000
   7.500   0.9619   0.05982   0.04941  -0.1044   0.5371   1.0000
   8.000   0.9946   0.06199   0.05180  -0.1029   0.5207   1.0000
   8.250   0.9947   0.06452   0.05441  -0.1017   0.5085   1.0000
   8.500   1.0284   0.06391   0.05394  -0.1014   0.5041   1.0000
   8.750   1.0276   0.06657   0.05671  -0.1003   0.4913   1.0000
   9.000   1.0642   0.06547   0.05577  -0.0998   0.4874   1.0000
   9.250   1.0624   0.06825   0.05865  -0.0987   0.4739   1.0000
   9.750   1.1000   0.06937   0.06008  -0.0970   0.4567   1.0000
  10.000   1.1010   0.07191   0.06274  -0.0960   0.4433   1.0000
  10.500   1.1407   0.07241   0.06357  -0.0941   0.4255   1.0000
  11.000   1.1521   0.07634   0.06779  -0.0923   0.3999   1.0000
  11.250   1.1883   0.07406   0.06571  -0.0908   0.3936   1.0000
  11.750   1.2014   0.07762   0.06958  -0.0890   0.3665   1.0000
  12.000   1.2171   0.07806   0.07018  -0.0879   0.3543   1.0000
  12.250   1.2543   0.07525   0.06754  -0.0861   0.3444   1.0000
  12.500   1.2702   0.07555   0.06799  -0.0849   0.3299   1.0000
  12.750   1.2836   0.07622   0.06877  -0.0837   0.3142   1.0000
  13.000   1.2937   0.07740   0.07002  -0.0827   0.2975   1.0000
  13.250   1.2989   0.07941   0.07210  -0.0820   0.2802   1.0000
  13.500   1.3038   0.08148   0.07425  -0.0813   0.2625   1.0000
  13.750   1.3087   0.08363   0.07642  -0.0807   0.2448   1.0000
  14.000   1.3125   0.08597   0.07875  -0.0802   0.2273   1.0000
  14.250   1.3147   0.08862   0.08138  -0.0798   0.2106   1.0000
  14.500   1.3152   0.09162   0.08436  -0.0797   0.1946   1.0000
  14.750   1.3143   0.09495   0.08768  -0.0798   0.1797   1.0000
  15.000   1.3124   0.09854   0.09127  -0.0802   0.1657   1.0000
  15.250   1.3102   0.10228   0.09504  -0.0807   0.1528   1.0000
  15.500   1.3083   0.10604   0.09881  -0.0813   0.1409   1.0000
  15.750   1.3069   0.10974   0.10249  -0.0820   0.1299   1.0000
  16.000   1.3070   0.11314   0.10581  -0.0827   0.1199   1.0000
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