Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER 433 AIRFOIL (e433-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 433 AIRFOIL (e433-il)
Reynolds number: 200,000
Max Cl/Cd: 76.49 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e433-il-200000-n5.txt
Download as CSV file: xf-e433-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 433 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
  ------ -------- --------- --------- -------- -------- --------
 -10.500  -0.1822   0.09474   0.09096  -0.0963   0.9534   0.0114
 -10.250  -0.1763   0.08978   0.08602  -0.1001   0.9496   0.0114
 -10.000  -0.1655   0.08577   0.08201  -0.1039   0.9470   0.0111
  -9.750  -0.1602   0.08042   0.07667  -0.1084   0.9429   0.0111
  -9.500  -0.1549   0.07555   0.07180  -0.1128   0.9376   0.0109
  -9.250  -0.1619   0.06278   0.05902  -0.1260   0.9324   0.0114
  -9.000  -0.1556   0.05972   0.05592  -0.1300   0.9258   0.0108
  -8.750  -0.1639   0.05273   0.04876  -0.1368   0.9179   0.0107
  -8.500  -0.1838   0.04762   0.04343  -0.1373   0.9069   0.0110
  -8.250  -0.1872   0.04305   0.03856  -0.1382   0.9008   0.0109
  -8.000  -0.1948   0.03969   0.03493  -0.1360   0.8919   0.0109
  -7.750  -0.1947   0.03490   0.02958  -0.1350   0.8867   0.0112
  -7.500  -0.1946   0.03189   0.02610  -0.1321   0.8794   0.0114
  -7.250  -0.1814   0.02934   0.02316  -0.1310   0.8748   0.0114
  -7.000  -0.1621   0.02687   0.02024  -0.1307   0.8716   0.0114
  -6.750  -0.1476   0.02521   0.01827  -0.1289   0.8665   0.0114
  -6.500  -0.1280   0.02354   0.01627  -0.1278   0.8622   0.0114
  -6.250  -0.1035   0.02204   0.01450  -0.1276   0.8590   0.0116
  -6.000  -0.0769   0.02073   0.01303  -0.1278   0.8565   0.0119
  -5.750  -0.0575   0.01988   0.01209  -0.1265   0.8521   0.0122
  -5.500  -0.0357   0.01911   0.01123  -0.1256   0.8478   0.0126
  -5.250  -0.0107   0.01828   0.01030  -0.1253   0.8445   0.0132
  -5.000   0.0161   0.01752   0.00942  -0.1254   0.8419   0.0140
  -4.750   0.0382   0.01691   0.00873  -0.1246   0.8382   0.0151
  -4.500   0.0591   0.01649   0.00829  -0.1236   0.8335   0.0167
  -4.250   0.0846   0.01602   0.00778  -0.1234   0.8301   0.0202
  -4.000   0.1122   0.01551   0.00721  -0.1237   0.8274   0.0257
  -3.750   0.1391   0.01498   0.00671  -0.1238   0.8246   0.0395
  -3.500   0.1587   0.01462   0.00648  -0.1226   0.8195   0.0682
  -3.250   0.1831   0.01407   0.00620  -0.1226   0.8158   0.1325
  -3.000   0.2096   0.01327   0.00588  -0.1232   0.8128   0.2593
  -2.750   0.2362   0.01215   0.00559  -0.1241   0.8104   0.4864
  -2.500   0.2512   0.01205   0.00612  -0.1211   0.8053   0.6543
  -2.250   0.2757   0.01222   0.00626  -0.1201   0.8013   0.7009
  -2.000   0.3034   0.01235   0.00632  -0.1198   0.7981   0.7266
  -1.750   0.3328   0.01246   0.00633  -0.1198   0.7955   0.7444
  -1.500   0.3537   0.01266   0.00649  -0.1183   0.7905   0.7581
  -1.250   0.3752   0.01291   0.00671  -0.1165   0.7860   0.7763
  -1.000   0.3989   0.01312   0.00688  -0.1150   0.7825   0.7932
  -0.750   0.4281   0.01316   0.00683  -0.1151   0.7797   0.8021
  -0.500   0.4472   0.01325   0.00691  -0.1134   0.7737   0.8062
  -0.250   0.4751   0.01323   0.00682  -0.1136   0.7694   0.8098
   0.000   0.5072   0.01316   0.00665  -0.1146   0.7660   0.8132
   0.250   0.5317   0.01319   0.00664  -0.1142   0.7609   0.8159
   0.500   0.5563   0.01319   0.00662  -0.1136   0.7555   0.8183
   0.750   0.5862   0.01313   0.00650  -0.1141   0.7514   0.8206
   1.000   0.6113   0.01314   0.00650  -0.1138   0.7460   0.8233
   1.250   0.6372   0.01315   0.00649  -0.1136   0.7402   0.8263
   1.500   0.6689   0.01310   0.00637  -0.1146   0.7358   0.8292
   1.750   0.6917   0.01314   0.00643  -0.1138   0.7293   0.8314
   2.000   0.7178   0.01312   0.00641  -0.1135   0.7233   0.8335
   2.250   0.7452   0.01310   0.00638  -0.1136   0.7176   0.8359
   2.500   0.7683   0.01314   0.00644  -0.1128   0.7101   0.8389
   2.750   0.7987   0.01310   0.00636  -0.1135   0.7043   0.8416
   3.000   0.8214   0.01317   0.00646  -0.1127   0.6958   0.8446
   3.250   0.8496   0.01314   0.00643  -0.1129   0.6891   0.8467
   3.500   0.8706   0.01320   0.00653  -0.1117   0.6799   0.8493
   3.750   0.8956   0.01322   0.00657  -0.1112   0.6716   0.8522
   4.000   0.9204   0.01325   0.00660  -0.1108   0.6620   0.8554
   4.250   0.9433   0.01333   0.00672  -0.1100   0.6515   0.8587
   4.500   0.9670   0.01339   0.00679  -0.1094   0.6408   0.8614
   4.750   0.9896   0.01345   0.00685  -0.1084   0.6292   0.8642
   5.000   1.0102   0.01354   0.00698  -0.1071   0.6162   0.8674
   5.250   1.0304   0.01367   0.00711  -0.1058   0.6021   0.8713
   5.500   1.0504   0.01381   0.00725  -0.1045   0.5868   0.8755
   5.750   1.0669   0.01396   0.00740  -0.1024   0.5707   0.8792
   6.000   1.0831   0.01416   0.00759  -0.1003   0.5526   0.8834
   6.250   1.0995   0.01444   0.00785  -0.0984   0.5330   0.8882
   6.500   1.1139   0.01476   0.00812  -0.0960   0.5124   0.8928
   6.750   1.1267   0.01514   0.00846  -0.0934   0.4916   0.8985
   7.000   1.1393   0.01558   0.00885  -0.0910   0.4693   0.9051
   7.250   1.1490   0.01605   0.00927  -0.0880   0.4489   0.9123
   7.500   1.1597   0.01657   0.00976  -0.0853   0.4273   0.9205
   7.750   1.1687   0.01712   0.01028  -0.0824   0.4064   0.9314
   8.250   1.1904   0.01834   0.01147  -0.0779   0.3646   1.0000
   8.500   1.2022   0.01922   0.01227  -0.0762   0.3431   1.0000
   8.750   1.2142   0.02011   0.01311  -0.0746   0.3222   1.0000
   9.000   1.2251   0.02108   0.01404  -0.0728   0.3010   1.0000
   9.250   1.2350   0.02213   0.01502  -0.0710   0.2813   1.0000
   9.500   1.2455   0.02318   0.01603  -0.0694   0.2610   1.0000
   9.750   1.2555   0.02429   0.01710  -0.0677   0.2423   1.0000
  10.000   1.2646   0.02548   0.01825  -0.0661   0.2242   1.0000
  10.250   1.2735   0.02672   0.01946  -0.0644   0.2070   1.0000
  10.500   1.2827   0.02798   0.02070  -0.0629   0.1897   1.0000
  10.750   1.2914   0.02930   0.02199  -0.0614   0.1733   1.0000
  11.000   1.2996   0.03069   0.02337  -0.0600   0.1577   1.0000
  11.250   1.3074   0.03216   0.02481  -0.0585   0.1428   1.0000
  11.500   1.3148   0.03369   0.02632  -0.0572   0.1287   1.0000
  11.750   1.3219   0.03528   0.02792  -0.0559   0.1157   1.0000
  12.000   1.3288   0.03694   0.02958  -0.0546   0.1040   1.0000
  12.250   1.3352   0.03868   0.03133  -0.0534   0.0934   1.0000
  12.500   1.3407   0.04054   0.03320  -0.0523   0.0838   1.0000
  12.750   1.3470   0.04239   0.03508  -0.0513   0.0750   1.0000
  13.000   1.3528   0.04433   0.03708  -0.0503   0.0673   1.0000
  13.250   1.3569   0.04649   0.03927  -0.0494   0.0606   1.0000
  13.500   1.3618   0.04862   0.04148  -0.0486   0.0542   1.0000
  13.750   1.3652   0.05096   0.04388  -0.0479   0.0491   1.0000
  14.000   1.3684   0.05339   0.04639  -0.0472   0.0443   1.0000
  14.250   1.3705   0.05601   0.04908  -0.0467   0.0403   1.0000
  14.500   1.3729   0.05866   0.05183  -0.0463   0.0366   1.0000
  14.750   1.3723   0.06173   0.05496  -0.0460   0.0337   1.0000
  15.000   1.3746   0.06454   0.05792  -0.0459   0.0309   1.0000
  15.250   1.3739   0.06781   0.06126  -0.0459   0.0285   1.0000
  15.500   1.3721   0.07131   0.06488  -0.0461   0.0266   1.0000
  15.750   1.3722   0.07464   0.06836  -0.0464   0.0247   1.0000
  16.000   1.3700   0.07835   0.07219  -0.0469   0.0230   1.0000
  16.250   1.3642   0.08268   0.07659  -0.0477   0.0217   1.0000
  16.500   1.3633   0.08643   0.08052  -0.0485   0.0202   1.0000
  16.750   1.3603   0.09054   0.08477  -0.0495   0.0189   1.0000
  17.000   1.3550   0.09509   0.08944  -0.0509   0.0178   1.0000
  17.250   1.3478   0.10006   0.09451  -0.0525   0.0170   1.0000
  17.500   1.3443   0.10451   0.09914  -0.0540   0.0158   1.0000
  17.750   1.3395   0.10925   0.10403  -0.0559   0.0149   1.0000
  18.000   1.3333   0.11434   0.10925  -0.0581   0.0141   1.0000
  18.250   1.3247   0.11990   0.11491  -0.0606   0.0135   1.0000
  18.500   1.3187   0.12506   0.12022  -0.0630   0.0128   1.0000
  18.750   1.3132   0.13022   0.12555  -0.0656   0.0120   1.0000
  19.000   1.3069   0.13563   0.13109  -0.0685   0.0113   1.0000
  19.250   1.2996   0.14130   0.13689  -0.0717   0.0108   1.0000
<< Back to EPPLER 433 AIRFOIL (e433-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER 433 AIRFOIL (e433-il)