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EPPLER 435 AIRFOIL (e435-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 435 AIRFOIL (e435-il)
Reynolds number: 200,000
Max Cl/Cd: 79.31 at α=8°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e435-il-200000.txt
Download as CSV file: xf-e435-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 435 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
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.1977   0.12400   0.12050  -0.0797   0.9758   0.0429
 -11.500  -0.1981   0.11765   0.11417  -0.0886   0.9725   0.0450
 -11.250  -0.1942   0.11178   0.10832  -0.0938   0.9685   0.0456
 -11.000  -0.1731   0.10908   0.10560  -0.0937   0.9645   0.0464
 -10.750  -0.1547   0.10572   0.10223  -0.0963   0.9617   0.0476
 -10.500  -0.1397   0.10139   0.09789  -0.1006   0.9594   0.0499
 -10.000  -0.1498   0.08630   0.08287  -0.1181   0.9478   0.0537
  -9.750  -0.1225   0.08472   0.08126  -0.1173   0.9465   0.0548
  -9.500  -0.1016   0.08144   0.07796  -0.1204   0.9449   0.0566
  -9.250  -0.0975   0.07684   0.07337  -0.1245   0.9377   0.0589
  -7.750  -0.1777   0.03773   0.03194  -0.1485   0.8856   0.0326
  -7.500  -0.1505   0.03385   0.02811  -0.1503   0.8834   0.0303
  -7.250  -0.1515   0.03065   0.02428  -0.1461   0.8748   0.0266
  -7.000  -0.1282   0.02817   0.02147  -0.1462   0.8709   0.0259
  -6.750  -0.0989   0.02585   0.01878  -0.1469   0.8682   0.0254
  -6.500  -0.0764   0.02441   0.01710  -0.1461   0.8639   0.0256
  -6.250  -0.0601   0.02346   0.01599  -0.1441   0.8580   0.0262
  -6.000  -0.0321   0.02231   0.01465  -0.1441   0.8547   0.0272
  -5.750  -0.0023   0.02117   0.01354  -0.1448   0.8520   0.0299
  -5.500   0.0207   0.02051   0.01283  -0.1442   0.8480   0.0336
  -5.250   0.0353   0.02015   0.01250  -0.1422   0.8419   0.0371
  -5.000   0.0611   0.01923   0.01161  -0.1423   0.8384   0.0437
  -4.750   0.0916   0.01826   0.01068  -0.1435   0.8357   0.0623
  -4.500   0.1151   0.01731   0.00998  -0.1438   0.8317   0.1039
  -4.250   0.1331   0.01627   0.00958  -0.1437   0.8259   0.2264
  -4.000   0.1617   0.01512   0.00970  -0.1452   0.8225   0.5414
  -3.750   0.1936   0.01548   0.01000  -0.1453   0.8198   0.5950
  -3.500   0.2263   0.01589   0.01028  -0.1455   0.8176   0.6230
  -3.250   0.2381   0.01658   0.01099  -0.1422   0.8110   0.6378
  -3.000   0.2621   0.01701   0.01137  -0.1408   0.8070   0.6525
  -2.750   0.2907   0.01732   0.01161  -0.1402   0.8041   0.6659
  -2.500   0.3221   0.01753   0.01171  -0.1403   0.8019   0.6786
  -2.250   0.3348   0.01808   0.01227  -0.1372   0.7959   0.6875
  -2.000   0.3556   0.01840   0.01258  -0.1353   0.7914   0.6980
  -1.750   0.3834   0.01861   0.01272  -0.1348   0.7883   0.7110
  -1.500   0.4108   0.01876   0.01282  -0.1338   0.7859   0.7189
  -1.250   0.4316   0.01898   0.01299  -0.1331   0.7806   0.7270
  -1.000   0.4506   0.01913   0.01313  -0.1313   0.7756   0.7309
  -0.750   0.4809   0.01906   0.01299  -0.1318   0.7724   0.7355
  -0.500   0.5186   0.01887   0.01268  -0.1341   0.7700   0.7407
  -0.250   0.5433   0.01895   0.01272  -0.1339   0.7656   0.7444
   0.000   0.5611   0.01912   0.01291  -0.1323   0.7598   0.7474
   0.250   0.5922   0.01901   0.01274  -0.1330   0.7563   0.7507
   0.500   0.6289   0.01882   0.01248  -0.1350   0.7538   0.7543
   0.750   0.6576   0.01890   0.01250  -0.1358   0.7494   0.7582
   1.000   0.6768   0.01904   0.01267  -0.1345   0.7432   0.7611
   1.250   0.7081   0.01889   0.01250  -0.1353   0.7397   0.7638
   1.500   0.7446   0.01869   0.01224  -0.1370   0.7370   0.7666
   1.750   0.7646   0.01892   0.01250  -0.1360   0.7311   0.7701
   2.000   0.7924   0.01894   0.01251  -0.1365   0.7258   0.7742
   2.250   0.8276   0.01871   0.01225  -0.1380   0.7223   0.7770
   2.500   0.8647   0.01847   0.01196  -0.1397   0.7195   0.7795
   2.750   0.8758   0.01880   0.01240  -0.1370   0.7114   0.7828
   3.000   0.9093   0.01862   0.01220  -0.1382   0.7071   0.7863
   3.250   0.9491   0.01836   0.01189  -0.1406   0.7039   0.7904
   3.500   0.9634   0.01861   0.01224  -0.1385   0.6962   0.7939
   3.750   0.9936   0.01843   0.01208  -0.1389   0.6912   0.7970
   4.000   1.0316   0.01814   0.01176  -0.1408   0.6876   0.8005
   4.250   1.0473   0.01837   0.01209  -0.1390   0.6794   0.8048
   4.500   1.0813   0.01813   0.01185  -0.1402   0.6741   0.8087
   4.750   1.1085   0.01801   0.01177  -0.1401   0.6684   0.8125
   5.000   1.1292   0.01801   0.01185  -0.1389   0.6607   0.8171
   5.250   1.1676   0.01769   0.01151  -0.1409   0.6556   0.8216
   5.500   1.1823   0.01782   0.01175  -0.1387   0.6465   0.8261
   5.750   1.2154   0.01751   0.01144  -0.1395   0.6403   0.8303
   6.000   1.2311   0.01760   0.01165  -0.1374   0.6309   0.8357
   6.250   1.2660   0.01733   0.01135  -0.1388   0.6238   0.8410
   6.500   1.2771   0.01741   0.01157  -0.1357   0.6135   0.8469
   6.750   1.3028   0.01732   0.01152  -0.1353   0.6046   0.8533
   7.000   1.3222   0.01726   0.01152  -0.1338   0.5941   0.8595
   7.250   1.3366   0.01733   0.01168  -0.1314   0.5827   0.8668
   7.500   1.3549   0.01733   0.01173  -0.1296   0.5712   0.8744
   7.750   1.3719   0.01731   0.01173  -0.1276   0.5590   0.8835
   8.000   1.3807   0.01741   0.01187  -0.1241   0.5456   0.8945
   8.250   1.3874   0.01759   0.01212  -0.1203   0.5315   0.9088
   8.500   1.3935   0.01777   0.01237  -0.1165   0.5168   0.9301
   8.750   1.4043   0.01798   0.01262  -0.1138   0.5006   1.0000
   9.000   1.4212   0.01854   0.01313  -0.1128   0.4825   1.0000
   9.250   1.4341   0.01923   0.01378  -0.1111   0.4636   1.0000
   9.500   1.4432   0.02006   0.01458  -0.1089   0.4440   1.0000
   9.750   1.4506   0.02100   0.01546  -0.1065   0.4241   1.0000
  10.000   1.4564   0.02205   0.01644  -0.1039   0.4045   1.0000
  10.250   1.4608   0.02323   0.01753  -0.1012   0.3852   1.0000
  10.500   1.4638   0.02454   0.01881  -0.0986   0.3655   1.0000
  10.750   1.4662   0.02596   0.02019  -0.0960   0.3462   1.0000
  11.000   1.4679   0.02750   0.02168  -0.0934   0.3275   1.0000
  11.250   1.4688   0.02917   0.02329  -0.0910   0.3092   1.0000
  11.500   1.4696   0.03094   0.02500  -0.0887   0.2916   1.0000
  11.750   1.4702   0.03281   0.02681  -0.0866   0.2746   1.0000
  12.000   1.4712   0.03474   0.02873  -0.0847   0.2576   1.0000
  12.250   1.4720   0.03678   0.03075  -0.0829   0.2411   1.0000
  12.500   1.4725   0.03892   0.03287  -0.0812   0.2254   1.0000
  12.750   1.4727   0.04119   0.03512  -0.0796   0.2100   1.0000
  13.000   1.4726   0.04356   0.03746  -0.0782   0.1954   1.0000
  13.250   1.4723   0.04604   0.03993  -0.0770   0.1814   1.0000
  13.500   1.4715   0.04867   0.04252  -0.0758   0.1682   1.0000
  13.750   1.4711   0.05134   0.04519  -0.0748   0.1553   1.0000
  14.000   1.4713   0.05405   0.04793  -0.0740   0.1431   1.0000
  14.250   1.4713   0.05686   0.05076  -0.0733   0.1317   1.0000
  14.500   1.4703   0.05987   0.05378  -0.0726   0.1212   1.0000
  14.750   1.4672   0.06316   0.05704  -0.0721   0.1120   1.0000
  15.000   1.4661   0.06636   0.06027  -0.0718   0.1028   1.0000
  15.250   1.4653   0.06959   0.06357  -0.0716   0.0943   1.0000
  15.500   1.4612   0.07328   0.06722  -0.0714   0.0872   1.0000
  15.750   1.4605   0.07667   0.07071  -0.0715   0.0801   1.0000
  16.000   1.4576   0.08036   0.07443  -0.0716   0.0741   1.0000
  16.250   1.4551   0.08411   0.07823  -0.0720   0.0686   1.0000
  16.500   1.4530   0.08783   0.08202  -0.0723   0.0636   1.0000
  16.750   1.4509   0.09165   0.08590  -0.0729   0.0591   1.0000
  17.000   1.4483   0.09549   0.08978  -0.0735   0.0552   1.0000
  17.250   1.4470   0.09932   0.09371  -0.0743   0.0514   1.0000
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