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EPPLER 393 AIRFOIL (e393-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 393 AIRFOIL (e393-il)
Reynolds number: 1,000,000
Max Cl/Cd: 152.69 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e393-il-1000000.txt
Download as CSV file: xf-e393-il-1000000.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 =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3321   0.11588   0.11424  -0.0380   1.0000   0.0087
 -10.750  -0.3308   0.11253   0.11090  -0.0386   1.0000   0.0095
  -8.500  -0.3776   0.02559   0.02285  -0.1162   0.9610   0.0075
  -8.250  -0.3549   0.02237   0.01925  -0.1185   0.9504   0.0075
  -8.000  -0.3304   0.01975   0.01626  -0.1200   0.9375   0.0075
  -7.750  -0.3068   0.01718   0.01331  -0.1209   0.9202   0.0076
  -7.500  -0.2832   0.01530   0.01110  -0.1212   0.9013   0.0078
  -7.250  -0.2588   0.01429   0.00989  -0.1210   0.8820   0.0081
  -7.000  -0.2345   0.01328   0.00865  -0.1207   0.8634   0.0082
  -6.750  -0.2097   0.01246   0.00762  -0.1204   0.8461   0.0084
  -6.500  -0.1843   0.01184   0.00684  -0.1201   0.8301   0.0087
  -6.250  -0.1583   0.01131   0.00617  -0.1200   0.8152   0.0092
  -6.000  -0.1319   0.01088   0.00560  -0.1198   0.8012   0.0099
  -5.500  -0.0780   0.01022   0.00472  -0.1196   0.7756   0.0107
  -5.250  -0.0512   0.00946   0.00379  -0.1197   0.7642   0.0119
  -5.000  -0.0237   0.00917   0.00342  -0.1197   0.7536   0.0130
  -4.750   0.0040   0.00896   0.00313  -0.1197   0.7437   0.0146
  -4.500   0.0319   0.00864   0.00275  -0.1198   0.7340   0.0184
  -4.250   0.0599   0.00851   0.00257  -0.1199   0.7252   0.0221
  -3.750   0.1163   0.00806   0.00204  -0.1201   0.7089   0.0372
  -3.500   0.1443   0.00787   0.00187  -0.1203   0.7014   0.0572
  -3.250   0.1728   0.00762   0.00173  -0.1206   0.6942   0.0902
  -3.000   0.2009   0.00741   0.00161  -0.1208   0.6874   0.1331
  -2.750   0.2294   0.00714   0.00149  -0.1212   0.6808   0.1871
  -2.500   0.2577   0.00692   0.00140  -0.1215   0.6743   0.2455
  -2.250   0.2863   0.00667   0.00133  -0.1218   0.6684   0.3144
  -2.000   0.3147   0.00645   0.00129  -0.1221   0.6624   0.3888
  -1.750   0.3432   0.00633   0.00128  -0.1224   0.6567   0.4445
  -1.500   0.3717   0.00626   0.00128  -0.1226   0.6509   0.4844
  -1.250   0.4000   0.00627   0.00128  -0.1227   0.6455   0.5068
  -1.000   0.4287   0.00625   0.00128  -0.1228   0.6401   0.5263
  -0.750   0.4571   0.00624   0.00129  -0.1230   0.6346   0.5491
  -0.500   0.4854   0.00626   0.00131  -0.1231   0.6294   0.5670
  -0.250   0.5140   0.00625   0.00132  -0.1232   0.6242   0.5836
   0.000   0.5423   0.00627   0.00134  -0.1233   0.6189   0.6007
   0.250   0.5706   0.00628   0.00138  -0.1234   0.6139   0.6183
   0.500   0.5991   0.00628   0.00141  -0.1236   0.6086   0.6355
   0.750   0.6272   0.00631   0.00145  -0.1236   0.6033   0.6540
   1.000   0.6555   0.00631   0.00150  -0.1238   0.5983   0.6739
   1.250   0.6837   0.00631   0.00155  -0.1238   0.5928   0.6953
   1.500   0.7115   0.00635   0.00162  -0.1238   0.5871   0.7182
   1.750   0.7396   0.00633   0.00167  -0.1239   0.5807   0.7429
   2.250   0.7947   0.00635   0.00182  -0.1238   0.5677   0.7958
   2.500   0.8214   0.00637   0.00190  -0.1236   0.5610   0.8266
   2.750   0.8476   0.00636   0.00198  -0.1232   0.5539   0.8617
   3.000   0.8712   0.00635   0.00205  -0.1221   0.5469   0.9045
   3.250   0.8952   0.00625   0.00207  -0.1212   0.5403   1.0000
   3.500   0.9231   0.00637   0.00215  -0.1213   0.5322   1.0000
   3.750   0.9512   0.00646   0.00223  -0.1214   0.5234   1.0000
   4.000   0.9788   0.00658   0.00233  -0.1214   0.5152   1.0000
   4.250   1.0066   0.00669   0.00244  -0.1215   0.5061   1.0000
   4.500   1.0341   0.00681   0.00255  -0.1215   0.4963   1.0000
   4.750   1.0611   0.00697   0.00267  -0.1215   0.4839   1.0000
   5.000   1.0880   0.00713   0.00281  -0.1214   0.4726   1.0000
   5.250   1.1146   0.00730   0.00296  -0.1213   0.4586   1.0000
   5.500   1.1410   0.00750   0.00313  -0.1211   0.4428   1.0000
   5.750   1.1656   0.00782   0.00333  -0.1207   0.4148   1.0000
   6.000   1.1879   0.00832   0.00363  -0.1199   0.3691   1.0000
   6.250   1.2082   0.00900   0.00404  -0.1188   0.3159   1.0000
   6.500   1.2286   0.00967   0.00449  -0.1177   0.2703   1.0000
   6.750   1.2482   0.01039   0.00498  -0.1166   0.2261   1.0000
   7.000   1.2660   0.01122   0.00554  -0.1151   0.1785   1.0000
   7.250   1.2844   0.01196   0.00607  -0.1138   0.1414   1.0000
   7.500   1.3023   0.01270   0.00662  -0.1123   0.1077   1.0000
   7.750   1.3207   0.01338   0.00716  -0.1110   0.0833   1.0000
   8.000   1.3385   0.01406   0.00772  -0.1095   0.0630   1.0000
   8.250   1.3565   0.01468   0.00827  -0.1081   0.0475   1.0000
   8.500   1.3717   0.01545   0.00892  -0.1062   0.0312   1.0000
   8.750   1.3829   0.01639   0.00974  -0.1036   0.0141   1.0000
   9.000   1.3919   0.01723   0.01055  -0.1006   0.0075   1.0000
   9.250   1.4049   0.01786   0.01122  -0.0982   0.0065   1.0000
   9.500   1.4156   0.01863   0.01204  -0.0956   0.0055   1.0000
   9.750   1.4253   0.01949   0.01298  -0.0929   0.0051   1.0000
  10.000   1.4372   0.02024   0.01381  -0.0907   0.0049   1.0000
  10.250   1.4479   0.02109   0.01474  -0.0884   0.0047   1.0000
  10.500   1.4571   0.02207   0.01580  -0.0861   0.0045   1.0000
  10.750   1.4658   0.02314   0.01694  -0.0839   0.0044   1.0000
  11.000   1.4741   0.02428   0.01815  -0.0818   0.0042   1.0000
  11.250   1.4816   0.02553   0.01948  -0.0798   0.0040   1.0000
  11.500   1.4881   0.02693   0.02096  -0.0779   0.0039   1.0000
  11.750   1.4940   0.02845   0.02256  -0.0761   0.0038   1.0000
  12.000   1.4985   0.03018   0.02438  -0.0744   0.0037   1.0000
  12.250   1.5021   0.03207   0.02637  -0.0728   0.0036   1.0000
  12.500   1.5042   0.03419   0.02860  -0.0713   0.0035   1.0000
  12.750   1.5060   0.03644   0.03094  -0.0701   0.0035   1.0000
  13.000   1.5064   0.03892   0.03353  -0.0689   0.0034   1.0000
  13.250   1.5058   0.04161   0.03633  -0.0680   0.0034   1.0000
  13.500   1.5039   0.04455   0.03938  -0.0672   0.0033   1.0000
  13.750   1.5009   0.04772   0.04267  -0.0666   0.0033   1.0000
  14.000   1.4971   0.05112   0.04618  -0.0661   0.0032   1.0000
  14.250   1.4915   0.05487   0.05005  -0.0659   0.0032   1.0000
  14.500   1.4880   0.05849   0.05379  -0.0659   0.0032   1.0000
  14.750   1.4795   0.06290   0.05835  -0.0660   0.0031   1.0000
  15.000   1.4742   0.06707   0.06264  -0.0664   0.0031   1.0000
  15.250   1.4678   0.07149   0.06719  -0.0670   0.0031   1.0000
  15.500   1.4568   0.07677   0.07264  -0.0677   0.0030   1.0000
  15.750   1.4494   0.08169   0.07771  -0.0688   0.0030   1.0000
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