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EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 654 AIRFOIL (e654-il)
Reynolds number: 1,000,000
Max Cl/Cd: 158.57 at α=6.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e654-il-1000000.txt
Download as CSV file: xf-e654-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 654 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
  ------ -------- --------- --------- -------- -------- --------
 -13.500  -0.2851   0.06722   0.06395  -0.1307   0.7495   0.0082
 -13.250  -0.3008   0.06015   0.05676  -0.1356   0.7462   0.0081
 -13.000  -0.3217   0.05331   0.04981  -0.1399   0.7427   0.0079
 -12.750  -0.3285   0.04901   0.04540  -0.1429   0.7385   0.0079
 -12.500  -0.3657   0.04166   0.03784  -0.1470   0.7352   0.0078
 -12.250  -0.3788   0.03802   0.03406  -0.1484   0.7320   0.0078
 -12.000  -0.3912   0.03486   0.03076  -0.1487   0.7288   0.0077
 -11.750  -0.4040   0.03197   0.02770  -0.1482   0.7254   0.0076
 -11.500  -0.4140   0.02950   0.02504  -0.1470   0.7222   0.0075
 -11.250  -0.4244   0.02706   0.02239  -0.1451   0.7188   0.0075
 -11.000  -0.4263   0.02534   0.02053  -0.1432   0.7167   0.0074
 -10.750  -0.4252   0.02402   0.01909  -0.1410   0.7142   0.0073
 -10.500  -0.4281   0.02263   0.01754  -0.1380   0.7117   0.0073
 -10.250  -0.4193   0.02136   0.01612  -0.1363   0.7091   0.0072
 -10.000  -0.4067   0.02028   0.01488  -0.1349   0.7066   0.0072
  -9.750  -0.3917   0.01928   0.01374  -0.1338   0.7039   0.0072
  -9.500  -0.3744   0.01841   0.01275  -0.1329   0.7016   0.0072
  -9.250  -0.3561   0.01751   0.01176  -0.1320   0.7001   0.0072
  -9.000  -0.3360   0.01675   0.01092  -0.1314   0.6984   0.0072
  -8.750  -0.3151   0.01604   0.01013  -0.1308   0.6966   0.0072
  -8.500  -0.2934   0.01538   0.00940  -0.1303   0.6947   0.0073
  -8.250  -0.2707   0.01480   0.00874  -0.1299   0.6927   0.0074
  -8.000  -0.2473   0.01426   0.00813  -0.1296   0.6907   0.0075
  -7.750  -0.2232   0.01378   0.00758  -0.1293   0.6888   0.0076
  -7.500  -0.1984   0.01335   0.00708  -0.1292   0.6866   0.0077
  -7.250  -0.1729   0.01296   0.00663  -0.1291   0.6847   0.0078
  -7.000  -0.1468   0.01258   0.00622  -0.1291   0.6835   0.0080
  -6.750  -0.1217   0.01201   0.00560  -0.1291   0.6821   0.0085
  -6.500  -0.0950   0.01165   0.00522  -0.1292   0.6804   0.0091
  -6.250  -0.0677   0.01137   0.00492  -0.1293   0.6787   0.0099
  -6.000  -0.0405   0.01102   0.00455  -0.1295   0.6770   0.0114
  -5.750  -0.0130   0.01072   0.00424  -0.1297   0.6754   0.0144
  -5.500   0.0148   0.01045   0.00398  -0.1299   0.6739   0.0198
  -5.250   0.0428   0.01021   0.00376  -0.1302   0.6722   0.0277
  -5.000   0.0711   0.01003   0.00360  -0.1306   0.6703   0.0361
  -4.750   0.0997   0.00988   0.00347  -0.1310   0.6681   0.0468
  -4.500   0.1281   0.00965   0.00331  -0.1314   0.6670   0.0606
  -4.250   0.1567   0.00942   0.00317  -0.1318   0.6657   0.0786
  -4.000   0.1855   0.00919   0.00303  -0.1323   0.6643   0.1027
  -3.750   0.2143   0.00891   0.00290  -0.1329   0.6628   0.1415
  -3.500   0.2431   0.00856   0.00277  -0.1336   0.6612   0.2006
  -3.250   0.2723   0.00820   0.00264  -0.1343   0.6595   0.2706
  -3.000   0.3018   0.00789   0.00254  -0.1351   0.6579   0.3375
  -2.750   0.3316   0.00762   0.00245  -0.1359   0.6564   0.4041
  -2.500   0.3617   0.00735   0.00238  -0.1367   0.6547   0.4777
  -2.250   0.3919   0.00715   0.00238  -0.1376   0.6527   0.5565
  -2.000   0.4219   0.00710   0.00244  -0.1382   0.6510   0.6019
  -1.750   0.4515   0.00707   0.00246  -0.1386   0.6497   0.6285
  -1.500   0.4811   0.00707   0.00248  -0.1391   0.6483   0.6456
  -1.250   0.5106   0.00709   0.00251  -0.1395   0.6466   0.6596
  -1.000   0.5402   0.00711   0.00253  -0.1399   0.6448   0.6700
  -0.750   0.5697   0.00714   0.00255  -0.1403   0.6429   0.6786
  -0.500   0.5992   0.00718   0.00255  -0.1407   0.6410   0.6859
  -0.250   0.6284   0.00721   0.00259  -0.1411   0.6391   0.6931
   0.000   0.6580   0.00731   0.00264  -0.1415   0.6367   0.6999
   0.250   0.6873   0.00738   0.00270  -0.1419   0.6344   0.7057
   0.500   0.7161   0.00739   0.00274  -0.1422   0.6326   0.7111
   0.750   0.7452   0.00741   0.00277  -0.1426   0.6304   0.7165
   1.000   0.7743   0.00744   0.00279  -0.1429   0.6281   0.7212
   1.250   0.8030   0.00745   0.00281  -0.1432   0.6257   0.7258
   1.500   0.8318   0.00748   0.00285  -0.1435   0.6232   0.7301
   1.750   0.8608   0.00757   0.00289  -0.1439   0.6204   0.7343
   2.000   0.8898   0.00764   0.00296  -0.1443   0.6178   0.7378
   2.250   0.9180   0.00762   0.00299  -0.1445   0.6153   0.7418
   2.500   0.9464   0.00764   0.00303  -0.1448   0.6124   0.7453
   2.750   0.9748   0.00766   0.00307  -0.1450   0.6095   0.7487
   3.000   1.0032   0.00771   0.00310  -0.1453   0.6065   0.7519
   3.250   1.0317   0.00781   0.00316  -0.1456   0.6029   0.7547
   3.500   1.0596   0.00780   0.00321  -0.1458   0.6000   0.7576
   3.750   1.0875   0.00780   0.00326  -0.1460   0.5964   0.7604
   4.000   1.1151   0.00784   0.00331  -0.1462   0.5925   0.7632
   4.250   1.1424   0.00791   0.00337  -0.1463   0.5883   0.7661
   4.500   1.1700   0.00796   0.00345  -0.1464   0.5841   0.7689
   4.750   1.1975   0.00800   0.00351  -0.1466   0.5791   0.7716
   5.000   1.2240   0.00807   0.00357  -0.1465   0.5737   0.7743
   5.250   1.2508   0.00812   0.00367  -0.1465   0.5684   0.7771
   5.500   1.2772   0.00818   0.00376  -0.1465   0.5619   0.7798
   5.750   1.3023   0.00830   0.00387  -0.1462   0.5553   0.7828
   6.000   1.3284   0.00838   0.00398  -0.1461   0.5474   0.7858
   6.250   1.3526   0.00853   0.00411  -0.1457   0.5388   0.7886
   6.500   1.3763   0.00868   0.00426  -0.1451   0.5280   0.7914
   6.750   1.3987   0.00885   0.00443  -0.1444   0.5155   0.7946
   7.000   1.4193   0.00908   0.00465  -0.1433   0.5016   0.7979
   7.250   1.4376   0.00938   0.00490  -0.1417   0.4851   0.8016
   7.500   1.4526   0.00975   0.00521  -0.1396   0.4665   0.8052
   8.000   1.4692   0.01064   0.00599  -0.1328   0.4285   0.8132
   8.250   1.4768   0.01119   0.00648  -0.1294   0.4096   0.8177
   8.500   1.4840   0.01180   0.00703  -0.1261   0.3922   0.8224
   8.750   1.4889   0.01249   0.00768  -0.1226   0.3744   0.8276
   9.000   1.4929   0.01328   0.00844  -0.1191   0.3577   0.8334
   9.250   1.4965   0.01419   0.00930  -0.1158   0.3412   0.8393
   9.500   1.4989   0.01521   0.01030  -0.1125   0.3252   0.8457
   9.750   1.5023   0.01631   0.01138  -0.1096   0.3105   0.8530
  10.000   1.5048   0.01754   0.01259  -0.1067   0.2955   0.8608
  10.250   1.5077   0.01883   0.01387  -0.1041   0.2817   0.8705
  10.500   1.5096   0.02021   0.01525  -0.1015   0.2679   0.8828
  10.750   1.5105   0.02166   0.01671  -0.0988   0.2539   0.9007
  11.000   1.5111   0.02296   0.01811  -0.0960   0.2413   1.0000
  11.250   1.5167   0.02446   0.01956  -0.0944   0.2284   1.0000
  11.500   1.5221   0.02600   0.02106  -0.0928   0.2161   1.0000
  11.750   1.5263   0.02766   0.02268  -0.0911   0.2039   1.0000
  12.000   1.5301   0.02937   0.02436  -0.0895   0.1922   1.0000
  12.250   1.5343   0.03111   0.02605  -0.0880   0.1805   1.0000
  12.500   1.5401   0.03278   0.02769  -0.0867   0.1699   1.0000
  12.750   1.5463   0.03443   0.02933  -0.0855   0.1600   1.0000
  13.000   1.5504   0.03633   0.03118  -0.0843   0.1502   1.0000
  13.250   1.5566   0.03807   0.03291  -0.0832   0.1406   1.0000
  13.500   1.5628   0.03987   0.03470  -0.0822   0.1323   1.0000
  13.750   1.5679   0.04178   0.03657  -0.0812   0.1235   1.0000
  14.000   1.5733   0.04372   0.03850  -0.0804   0.1153   1.0000
  14.250   1.5794   0.04564   0.04040  -0.0796   0.1073   1.0000
  14.750   1.5897   0.04976   0.04451  -0.0781   0.0929   1.0000
  15.000   1.5941   0.05194   0.04667  -0.0775   0.0856   1.0000
  15.250   1.5982   0.05422   0.04895  -0.0769   0.0796   1.0000
  15.500   1.6039   0.05636   0.05110  -0.0764   0.0735   1.0000
  15.750   1.6056   0.05899   0.05370  -0.0759   0.0672   1.0000
  16.000   1.6114   0.06118   0.05592  -0.0756   0.0625   1.0000
  16.250   1.6139   0.06382   0.05856  -0.0753   0.0578   1.0000
  16.500   1.6178   0.06632   0.06108  -0.0751   0.0531   1.0000
  16.750   1.6204   0.06904   0.06381  -0.0749   0.0489   1.0000
  17.000   1.6229   0.07180   0.06658  -0.0748   0.0450   1.0000
  17.250   1.6252   0.07462   0.06944  -0.0748   0.0414   1.0000
  17.500   1.6267   0.07760   0.07243  -0.0749   0.0382   1.0000
  17.750   1.6291   0.08053   0.07541  -0.0751   0.0357   1.0000
  18.000   1.6300   0.08366   0.07857  -0.0753   0.0328   1.0000
  18.250   1.6310   0.08685   0.08181  -0.0757   0.0307   1.0000
  18.500   1.6325   0.08998   0.08498  -0.0761   0.0286   1.0000
  18.750   1.6311   0.09358   0.08863  -0.0767   0.0266   1.0000
  19.000   1.6323   0.09684   0.09195  -0.0773   0.0249   1.0000
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