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EPPLER 654 AIRFOIL (e654-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 654 AIRFOIL (e654-il)
Reynolds number: 100,000
Max Cl/Cd: 28.31 at α=10.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e654-il-100000-n5.txt
Download as CSV file: xf-e654-il-100000-n5.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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.0774   0.09952   0.09371  -0.1152   0.8443   0.0252
 -11.500  -0.0787   0.09462   0.08881  -0.1179   0.8394   0.0257
 -11.250  -0.0824   0.08951   0.08372  -0.1203   0.8341   0.0255
 -10.750  -0.1533   0.06435   0.05845  -0.1351   0.8258   0.0223
 -10.500  -0.1873   0.05662   0.05052  -0.1410   0.8202   0.0223
 -10.250  -0.2058   0.05242   0.04615  -0.1431   0.8145   0.0222
 -10.000  -0.2232   0.04888   0.04239  -0.1438   0.8093   0.0221
  -9.750  -0.2404   0.04593   0.03919  -0.1430   0.8043   0.0222
  -9.500  -0.2553   0.04388   0.03693  -0.1407   0.7987   0.0222
  -9.250  -0.2673   0.04113   0.03373  -0.1387   0.7941   0.0226
  -9.000  -0.2632   0.03917   0.03151  -0.1375   0.7907   0.0229
  -8.750  -0.2543   0.03758   0.02973  -0.1364   0.7876   0.0234
  -8.500  -0.2453   0.03605   0.02801  -0.1350   0.7837   0.0238
  -8.250  -0.2332   0.03449   0.02621  -0.1338   0.7801   0.0244
  -8.000  -0.2182   0.03290   0.02433  -0.1328   0.7769   0.0252
  -7.750  -0.2000   0.03128   0.02239  -0.1319   0.7741   0.0262
  -7.500  -0.1797   0.03015   0.02110  -0.1314   0.7718   0.0276
  -7.250  -0.1631   0.02944   0.02031  -0.1303   0.7683   0.0297
  -7.000  -0.1452   0.02857   0.01930  -0.1292   0.7651   0.0318
  -6.750  -0.1263   0.02783   0.01852  -0.1283   0.7621   0.0340
  -6.500  -0.1062   0.02693   0.01749  -0.1274   0.7594   0.0367
  -6.250  -0.0849   0.02624   0.01677  -0.1268   0.7569   0.0405
  -6.000  -0.0624   0.02554   0.01600  -0.1264   0.7548   0.0461
  -5.750  -0.0443   0.02505   0.01551  -0.1253   0.7518   0.0528
  -5.500  -0.0274   0.02466   0.01514  -0.1241   0.7484   0.0611
  -5.250  -0.0081   0.02423   0.01472  -0.1232   0.7455   0.0730
  -5.000   0.0130   0.02374   0.01428  -0.1226   0.7427   0.0897
  -4.750   0.0363   0.02322   0.01383  -0.1223   0.7404   0.1146
  -4.500   0.0607   0.02265   0.01341  -0.1222   0.7383   0.1506
  -4.250   0.0861   0.02211   0.01304  -0.1224   0.7367   0.2025
  -4.000   0.1000   0.02203   0.01324  -0.1209   0.7328   0.2575
  -3.750   0.1179   0.02178   0.01331  -0.1201   0.7293   0.3321
  -3.500   0.1387   0.02145   0.01335  -0.1194   0.7264   0.4240
  -3.250   0.1600   0.02133   0.01362  -0.1180   0.7240   0.5181
  -3.000   0.1827   0.02154   0.01398  -0.1164   0.7220   0.5864
  -2.750   0.2090   0.02181   0.01417  -0.1156   0.7204   0.6324
  -2.500   0.2279   0.02233   0.01464  -0.1139   0.7175   0.6611
  -2.250   0.2399   0.02302   0.01531  -0.1116   0.7126   0.6834
  -2.000   0.2596   0.02347   0.01567  -0.1100   0.7093   0.7024
  -1.750   0.2820   0.02381   0.01592  -0.1088   0.7069   0.7191
  -1.500   0.3049   0.02410   0.01613  -0.1074   0.7049   0.7333
  -1.250   0.3302   0.02428   0.01621  -0.1065   0.7033   0.7465
  -1.000   0.3384   0.02503   0.01695  -0.1036   0.6984   0.7588
  -0.750   0.3471   0.02574   0.01766  -0.1008   0.6934   0.7707
  -0.500   0.3652   0.02604   0.01792  -0.0989   0.6904   0.7807
  -0.250   0.3912   0.02615   0.01793  -0.0985   0.6883   0.7919
   0.000   0.4167   0.02618   0.01788  -0.0977   0.6866   0.8008
   0.250   0.4468   0.02616   0.01776  -0.0980   0.6853   0.8095
   0.750   0.4486   0.02796   0.01962  -0.0907   0.6723   0.8265
   1.000   0.4755   0.02793   0.01953  -0.0903   0.6705   0.8334
   1.250   0.5093   0.02783   0.01934  -0.0915   0.6691   0.8404
   1.750   0.5069   0.02976   0.02133  -0.0840   0.6551   0.8555
   2.000   0.5371   0.02958   0.02110  -0.0842   0.6535   0.8605
   2.250   0.5703   0.02938   0.02085  -0.0850   0.6522   0.8658
   2.750   0.5754   0.03156   0.02308  -0.0795   0.6375   0.8807
   3.000   0.5911   0.03227   0.02379  -0.0786   0.6324   0.8877
   3.250   0.6442   0.03086   0.02231  -0.0811   0.6352   0.8911
   3.750   0.6545   0.03303   0.02456  -0.0768   0.6201   0.9074
   4.000   0.6886   0.03251   0.02404  -0.0773   0.6190   0.9137
   4.500   0.6923   0.03541   0.02705  -0.0732   0.6003   0.9362
   5.500   0.7784   0.03776   0.02954  -0.0745   0.5755   1.0000
   5.750   0.8143   0.03735   0.02913  -0.0757   0.5736   1.0000
   6.000   0.8517   0.03675   0.02855  -0.0770   0.5722   1.0000
   6.500   0.8879   0.03835   0.03023  -0.0769   0.5575   1.0000
   7.000   0.9252   0.03976   0.03172  -0.0766   0.5429   1.0000
   7.250   0.9615   0.03895   0.03094  -0.0774   0.5411   1.0000
   7.500   0.9632   0.04100   0.03305  -0.0762   0.5283   1.0000
   7.750   0.9991   0.04012   0.03221  -0.0769   0.5261   1.0000
   8.750   1.0789   0.04186   0.03418  -0.0756   0.4953   1.0000
   9.000   1.0858   0.04346   0.03583  -0.0746   0.4831   1.0000
   9.250   1.1230   0.04225   0.03469  -0.0750   0.4792   1.0000
   9.500   1.1309   0.04376   0.03625  -0.0741   0.4667   1.0000
   9.750   1.1517   0.04406   0.03662  -0.0737   0.4574   1.0000
  10.000   1.1794   0.04370   0.03630  -0.0735   0.4492   1.0000
  10.250   1.1948   0.04452   0.03718  -0.0729   0.4373   1.0000
  10.500   1.2226   0.04414   0.03683  -0.0727   0.4278   1.0000
  10.750   1.2472   0.04406   0.03676  -0.0724   0.4165   1.0000
  11.000   1.2616   0.04496   0.03769  -0.0717   0.4031   1.0000
  11.250   1.2781   0.04568   0.03843  -0.0710   0.3899   1.0000
  11.500   1.2950   0.04635   0.03912  -0.0704   0.3765   1.0000
  11.750   1.3110   0.04712   0.03988  -0.0697   0.3628   1.0000
  12.000   1.3254   0.04805   0.04079  -0.0690   0.3489   1.0000
  12.250   1.3375   0.04921   0.04193  -0.0682   0.3348   1.0000
  12.500   1.3444   0.05095   0.04371  -0.0674   0.3208   1.0000
  12.750   1.3514   0.05273   0.04551  -0.0666   0.3071   1.0000
  13.000   1.3581   0.05458   0.04737  -0.0659   0.2936   1.0000
  13.250   1.3646   0.05646   0.04926  -0.0652   0.2805   1.0000
  13.500   1.3710   0.05839   0.05120  -0.0645   0.2679   1.0000
  13.750   1.3767   0.06041   0.05320  -0.0639   0.2555   1.0000
  14.000   1.3796   0.06286   0.05571  -0.0635   0.2432   1.0000
  14.250   1.3829   0.06531   0.05821  -0.0630   0.2315   1.0000
  14.500   1.3863   0.06776   0.06068  -0.0627   0.2203   1.0000
  14.750   1.3892   0.07027   0.06318  -0.0623   0.2097   1.0000
  15.000   1.3906   0.07314   0.06615  -0.0622   0.1989   1.0000
  15.250   1.3924   0.07598   0.06903  -0.0621   0.1889   1.0000
  15.500   1.3937   0.07883   0.07188  -0.0621   0.1797   1.0000
  15.750   1.3941   0.08200   0.07516  -0.0622   0.1700   1.0000
  16.000   1.3947   0.08511   0.07832  -0.0624   0.1615   1.0000
  16.250   1.3941   0.08843   0.08167  -0.0627   0.1531   1.0000
  16.500   1.3942   0.09177   0.08513  -0.0631   0.1451   1.0000
  16.750   1.3931   0.09521   0.08856  -0.0636   0.1379   1.0000
  17.000   1.3923   0.09879   0.09230  -0.0643   0.1303   1.0000
  17.250   1.3907   0.10239   0.09587  -0.0650   0.1240   1.0000
  17.500   1.3895   0.10612   0.09978  -0.0660   0.1171   1.0000
  17.750   1.3876   0.10984   0.10347  -0.0669   0.1115   1.0000
  18.000   1.3861   0.11371   0.10753  -0.0681   0.1053   1.0000
  18.500   1.3822   0.12149   0.11547  -0.0707   0.0949   1.0000
  18.750   1.3795   0.12554   0.11959  -0.0723   0.0901   1.0000
  19.000   1.3781   0.12941   0.12352  -0.0739   0.0856   1.0000
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