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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 200,000
Max Cl/Cd: 87.54 at α=7.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e393-il-200000.txt
Download as CSV file: xf-e393-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.3239   0.09280   0.08963  -0.0418   1.0000   0.0466
  -8.250  -0.3332   0.09083   0.08775  -0.0401   1.0000   0.0477
  -8.000  -0.3493   0.08954   0.08657  -0.0372   1.0000   0.0481
  -7.750  -0.3438   0.08566   0.08272  -0.0417   0.9961   0.0499
  -7.500  -0.3242   0.07304   0.07004  -0.0727   0.9784   0.0533
  -7.250  -0.3092   0.06369   0.06061  -0.0831   0.9711   0.0546
  -7.000  -0.2865   0.06189   0.05890  -0.0817   0.9652   0.0562
  -6.750  -0.2592   0.05734   0.05428  -0.0880   0.9586   0.0589
  -6.250  -0.1564   0.02709   0.02366  -0.1084   0.9263   0.0724
  -6.000  -0.1741   0.02801   0.02238  -0.1142   0.9317   0.0314
  -5.750  -0.1418   0.02437   0.01828  -0.1164   0.9248   0.0320
  -5.500  -0.1073   0.02244   0.01621  -0.1185   0.9184   0.0350
  -5.250  -0.0729   0.02007   0.01342  -0.1198   0.9113   0.0355
  -5.000  -0.0386   0.01831   0.01139  -0.1208   0.9039   0.0373
  -4.750  -0.0068   0.01701   0.00989  -0.1213   0.8949   0.0404
  -4.500   0.0262   0.01561   0.00844  -0.1224   0.8876   0.0479
  -4.250   0.0546   0.01462   0.00738  -0.1224   0.8766   0.0570
  -4.000   0.0838   0.01386   0.00659  -0.1228   0.8667   0.0718
  -3.750   0.1143   0.01300   0.00578  -0.1234   0.8581   0.1048
  -3.500   0.1419   0.01203   0.00520  -0.1239   0.8474   0.1967
  -3.250   0.1692   0.01128   0.00497  -0.1244   0.8377   0.3450
  -3.000   0.1974   0.01099   0.00495  -0.1244   0.8294   0.4624
  -2.750   0.2243   0.01097   0.00495  -0.1241   0.8196   0.5255
  -2.500   0.2514   0.01099   0.00495  -0.1237   0.8109   0.5647
  -2.250   0.2792   0.01100   0.00490  -0.1234   0.8030   0.5965
  -2.000   0.3056   0.01104   0.00492  -0.1229   0.7941   0.6247
  -1.750   0.3332   0.01106   0.00487  -0.1226   0.7873   0.6508
  -1.500   0.3591   0.01110   0.00491  -0.1220   0.7786   0.6746
  -1.250   0.3864   0.01113   0.00489  -0.1216   0.7719   0.6981
  -1.000   0.4120   0.01115   0.00493  -0.1210   0.7640   0.7201
  -0.750   0.4390   0.01119   0.00492  -0.1206   0.7576   0.7434
  -0.500   0.4637   0.01121   0.00498  -0.1198   0.7500   0.7651
  -0.250   0.4899   0.01124   0.00498  -0.1192   0.7442   0.7890
   0.000   0.5134   0.01126   0.00506  -0.1181   0.7366   0.8140
   0.250   0.5373   0.01126   0.00505  -0.1169   0.7310   0.8404
   0.500   0.5576   0.01126   0.00513  -0.1151   0.7238   0.8709
   0.750   0.5781   0.01119   0.00508  -0.1131   0.7181   0.9082
   1.000   0.6082   0.01110   0.00502  -0.1135   0.7116   0.9661
   1.250   0.6446   0.01120   0.00502  -0.1157   0.7052   1.0000
   1.500   0.6755   0.01138   0.00512  -0.1167   0.6993   1.0000
   1.750   0.7047   0.01155   0.00524  -0.1173   0.6925   1.0000
   2.000   0.7351   0.01173   0.00531  -0.1179   0.6875   1.0000
   2.250   0.7623   0.01192   0.00553  -0.1180   0.6802   1.0000
   2.500   0.7917   0.01209   0.00564  -0.1184   0.6746   1.0000
   2.750   0.8189   0.01230   0.00586  -0.1185   0.6677   1.0000
   3.000   0.8474   0.01246   0.00599  -0.1187   0.6615   1.0000
   3.250   0.8747   0.01265   0.00619  -0.1187   0.6546   1.0000
   3.500   0.9026   0.01280   0.00634  -0.1187   0.6474   1.0000
   3.750   0.9296   0.01298   0.00654  -0.1186   0.6399   1.0000
   4.000   0.9575   0.01311   0.00666  -0.1186   0.6327   1.0000
   4.250   0.9838   0.01328   0.00688  -0.1184   0.6244   1.0000
   4.500   1.0121   0.01339   0.00697  -0.1184   0.6169   1.0000
   4.750   1.0373   0.01354   0.00721  -0.1179   0.6075   1.0000
   5.000   1.0643   0.01366   0.00734  -0.1177   0.5990   1.0000
   5.250   1.0908   0.01374   0.00745  -0.1174   0.5893   1.0000
   5.500   1.1158   0.01385   0.00768  -0.1168   0.5788   1.0000
   5.750   1.1415   0.01396   0.00783  -0.1163   0.5685   1.0000
   6.000   1.1671   0.01404   0.00795  -0.1158   0.5574   1.0000
   6.250   1.1920   0.01411   0.00806  -0.1152   0.5448   1.0000
   6.500   1.2159   0.01421   0.00823  -0.1144   0.5312   1.0000
   6.750   1.2391   0.01434   0.00846  -0.1134   0.5161   1.0000
   7.000   1.2611   0.01447   0.00871  -0.1123   0.4978   1.0000
   7.250   1.2825   0.01465   0.00892  -0.1110   0.4766   1.0000
   7.500   1.3023   0.01490   0.00920  -0.1096   0.4506   1.0000
   7.750   1.3199   0.01529   0.00954  -0.1077   0.4181   1.0000
   8.000   1.3345   0.01587   0.01004  -0.1055   0.3759   1.0000
   8.250   1.3437   0.01679   0.01071  -0.1025   0.3226   1.0000
   8.500   1.3470   0.01808   0.01167  -0.0988   0.2665   1.0000
   8.750   1.3470   0.01951   0.01279  -0.0948   0.2155   1.0000
   9.000   1.3451   0.02096   0.01396  -0.0906   0.1735   1.0000
   9.250   1.3442   0.02247   0.01523  -0.0869   0.1392   1.0000
   9.500   1.3456   0.02395   0.01657  -0.0837   0.1129   1.0000
   9.750   1.3482   0.02547   0.01800  -0.0808   0.0915   1.0000
  10.000   1.3492   0.02719   0.01965  -0.0781   0.0725   1.0000
  10.250   1.3463   0.02934   0.02169  -0.0752   0.0539   1.0000
  10.500   1.3386   0.03209   0.02439  -0.0723   0.0378   1.0000
  10.750   1.3300   0.03512   0.02743  -0.0697   0.0303   1.0000
  11.000   1.3295   0.03760   0.03005  -0.0679   0.0263   1.0000
  11.250   1.3239   0.04069   0.03318  -0.0663   0.0238   1.0000
  11.500   1.3218   0.04359   0.03619  -0.0648   0.0221   1.0000
  11.750   1.3262   0.04590   0.03864  -0.0639   0.0204   1.0000
  12.000   1.3295   0.04838   0.04122  -0.0630   0.0190   1.0000
  12.250   1.3320   0.05102   0.04395  -0.0621   0.0181   1.0000
  12.500   1.3344   0.05379   0.04679  -0.0613   0.0174   1.0000
  12.750   1.3382   0.05660   0.04968  -0.0602   0.0167   1.0000
  13.000   1.3495   0.05954   0.05272  -0.0583   0.0160   1.0000
  13.250   1.3567   0.06223   0.05562  -0.0576   0.0158   1.0000
  13.500   1.3624   0.06523   0.05883  -0.0569   0.0156   1.0000
  13.750   1.3657   0.06862   0.06246  -0.0564   0.0155   1.0000
  14.000   1.3654   0.07248   0.06658  -0.0562   0.0154   1.0000
  14.250   1.3616   0.07679   0.07115  -0.0562   0.0154   1.0000
  14.500   1.3545   0.08156   0.07622  -0.0566   0.0154   1.0000
  14.750   1.3447   0.08679   0.08171  -0.0575   0.0154   1.0000
  15.000   1.3324   0.09247   0.08764  -0.0589   0.0155   1.0000
  15.250   1.3183   0.09858   0.09400  -0.0609   0.0156   1.0000
  15.500   1.3026   0.10517   0.10082  -0.0634   0.0157   1.0000
  15.750   1.2859   0.11222   0.10810  -0.0666   0.0158   1.0000
  16.000   1.2683   0.11977   0.11585  -0.0703   0.0159   1.0000
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