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EPPLER E662 AIRFOIL (e662-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: EPPLER E662 AIRFOIL (e662-il)
Reynolds number: 500,000
Max Cl/Cd: 114.27 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e662-il-500000.txt
Download as CSV file: xf-e662-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER E662 AIRFOIL                             
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.0559   0.09515   0.09197  -0.1449   0.8798   0.0249
 -12.000  -0.0536   0.09115   0.08797  -0.1469   0.8775   0.0250
 -11.750  -0.0525   0.08760   0.08441  -0.1473   0.8757   0.0258
 -11.500  -0.0447   0.08519   0.08197  -0.1484   0.8736   0.0262
 -11.250  -0.0407   0.08188   0.07865  -0.1502   0.8714   0.0264
 -11.000  -0.0334   0.07976   0.07654  -0.1509   0.8697   0.0276
 -10.750  -0.0333   0.07622   0.07302  -0.1525   0.8679   0.0283
 -10.500  -0.0411   0.07092   0.06776  -0.1554   0.8657   0.0299
  -9.250  -0.1741   0.04629   0.04258  -0.1602   0.8515   0.0313
  -9.000  -0.2065   0.04054   0.03661  -0.1566   0.8489   0.0319
  -8.750  -0.1966   0.03828   0.03436  -0.1559   0.8472   0.0325
  -8.500  -0.1832   0.03711   0.03319  -0.1551   0.8456   0.0333
  -8.250  -0.2129   0.02826   0.02336  -0.1484   0.8432   0.0242
  -8.000  -0.2054   0.02511   0.01985  -0.1464   0.8417   0.0233
  -7.750  -0.1911   0.02281   0.01721  -0.1449   0.8403   0.0227
  -7.500  -0.1732   0.02110   0.01525  -0.1436   0.8390   0.0226
  -7.250  -0.1525   0.01988   0.01386  -0.1428   0.8377   0.0229
  -7.000  -0.1304   0.01886   0.01269  -0.1421   0.8364   0.0233
  -6.750  -0.1072   0.01823   0.01195  -0.1415   0.8350   0.0241
  -6.500  -0.0834   0.01759   0.01120  -0.1410   0.8335   0.0246
  -6.250  -0.0593   0.01694   0.01046  -0.1406   0.8321   0.0248
  -6.000  -0.0360   0.01613   0.00958  -0.1400   0.8308   0.0252
  -5.750  -0.0140   0.01526   0.00868  -0.1393   0.8294   0.0259
  -5.500   0.0095   0.01474   0.00814  -0.1388   0.8281   0.0267
  -5.250   0.0341   0.01437   0.00774  -0.1386   0.8268   0.0277
  -5.000   0.0592   0.01414   0.00748  -0.1384   0.8255   0.0292
  -4.750   0.0825   0.01390   0.00723  -0.1378   0.8241   0.0305
  -4.500   0.1055   0.01363   0.00694  -0.1372   0.8223   0.0316
  -4.250   0.1287   0.01329   0.00660  -0.1367   0.8205   0.0342
  -4.000   0.1538   0.01310   0.00640  -0.1364   0.8187   0.0376
  -3.750   0.1790   0.01281   0.00616  -0.1362   0.8169   0.0505
  -3.500   0.2037   0.01227   0.00595  -0.1362   0.8152   0.1217
  -3.250   0.2300   0.01186   0.00580  -0.1365   0.8136   0.1973
  -3.000   0.2568   0.01137   0.00567  -0.1371   0.8121   0.3016
  -2.750   0.2845   0.01063   0.00554  -0.1381   0.8106   0.4796
  -2.500   0.3082   0.01011   0.00575  -0.1378   0.8086   0.6757
  -2.250   0.3320   0.01033   0.00608  -0.1368   0.8060   0.7360
  -2.000   0.3586   0.01054   0.00626  -0.1365   0.8037   0.7578
  -1.750   0.3859   0.01074   0.00642  -0.1363   0.8014   0.7720
  -1.500   0.4124   0.01097   0.00664  -0.1357   0.7994   0.7840
  -1.250   0.4383   0.01121   0.00687  -0.1348   0.7976   0.7935
  -1.000   0.4687   0.01134   0.00692  -0.1353   0.7959   0.8021
  -0.750   0.4929   0.01155   0.00714  -0.1343   0.7937   0.8065
  -0.500   0.5141   0.01171   0.00732  -0.1328   0.7902   0.8129
  -0.250   0.5384   0.01182   0.00743  -0.1319   0.7872   0.8199
   0.000   0.5614   0.01197   0.00758  -0.1305   0.7847   0.8264
   0.250   0.5903   0.01200   0.00758  -0.1306   0.7826   0.8337
   0.500   0.6161   0.01202   0.00758  -0.1298   0.7807   0.8374
   0.750   0.6418   0.01206   0.00762  -0.1294   0.7779   0.8408
   1.000   0.6656   0.01205   0.00763  -0.1288   0.7738   0.8447
   1.250   0.6969   0.01196   0.00751  -0.1298   0.7705   0.8478
   1.500   0.7252   0.01178   0.00731  -0.1299   0.7678   0.8493
   1.750   0.7562   0.01163   0.00714  -0.1306   0.7655   0.8508
   2.000   0.7816   0.01158   0.00710  -0.1302   0.7620   0.8527
   2.250   0.8056   0.01149   0.00705  -0.1296   0.7574   0.8546
   2.500   0.8349   0.01133   0.00688  -0.1301   0.7539   0.8564
   2.750   0.8679   0.01114   0.00666  -0.1313   0.7509   0.8580
   3.000   0.8947   0.01104   0.00659  -0.1313   0.7464   0.8598
   3.250   0.9216   0.01092   0.00649  -0.1314   0.7410   0.8617
   3.500   0.9530   0.01071   0.00627  -0.1323   0.7369   0.8629
   3.750   0.9760   0.01056   0.00617  -0.1315   0.7311   0.8641
   4.000   0.9998   0.01040   0.00605  -0.1307   0.7246   0.8656
   4.250   1.0251   0.01026   0.00593  -0.1303   0.7182   0.8670
   4.500   1.0474   0.01015   0.00586  -0.1294   0.7095   0.8683
   4.750   1.0696   0.01007   0.00581  -0.1283   0.6996   0.8701
   5.000   1.0927   0.00998   0.00573  -0.1275   0.6883   0.8717
   5.250   1.1145   0.00995   0.00568  -0.1265   0.6740   0.8732
   5.500   1.1352   0.00998   0.00568  -0.1253   0.6570   0.8747
   5.750   1.1530   0.01009   0.00571  -0.1235   0.6378   0.8763
   6.000   1.1657   0.01025   0.00580  -0.1206   0.6164   0.8781
   6.250   1.1759   0.01052   0.00600  -0.1173   0.5936   0.8798
   6.500   1.1850   0.01091   0.00630  -0.1139   0.5698   0.8815
   6.750   1.1926   0.01138   0.00667  -0.1103   0.5458   0.8834
   7.000   1.2005   0.01190   0.00711  -0.1070   0.5214   0.8855
   7.250   1.2067   0.01253   0.00764  -0.1034   0.4974   0.8879
   7.500   1.2145   0.01319   0.00823  -0.1004   0.4736   0.8900
   7.750   1.2215   0.01395   0.00890  -0.0974   0.4503   0.8918
   8.000   1.2263   0.01474   0.00961  -0.0940   0.4256   0.8937
   8.250   1.2332   0.01556   0.01036  -0.0912   0.4026   0.8957
   8.500   1.2390   0.01650   0.01120  -0.0883   0.3782   0.8978
   8.750   1.2470   0.01742   0.01205  -0.0858   0.3535   0.8999
   9.000   1.2544   0.01844   0.01297  -0.0834   0.3296   0.9023
   9.250   1.2646   0.01937   0.01383  -0.0815   0.3075   0.9046
   9.500   1.2729   0.02041   0.01478  -0.0794   0.2843   0.9066
   9.750   1.2814   0.02142   0.01570  -0.0773   0.2614   0.9087
  10.000   1.2898   0.02247   0.01667  -0.0753   0.2394   0.9110
  10.250   1.2979   0.02361   0.01771  -0.0733   0.2159   0.9134
  10.500   1.3074   0.02472   0.01875  -0.0716   0.1959   0.9158
  10.750   1.3169   0.02587   0.01983  -0.0700   0.1755   0.9182
  11.000   1.3248   0.02715   0.02099  -0.0682   0.1551   0.9207
  11.250   1.3340   0.02827   0.02208  -0.0666   0.1391   0.9235
  11.500   1.3425   0.02949   0.02325  -0.0649   0.1228   0.9268
  11.750   1.3510   0.03078   0.02448  -0.0634   0.1071   0.9305
  12.000   1.3598   0.03207   0.02575  -0.0619   0.0949   0.9344
  12.250   1.3682   0.03333   0.02700  -0.0603   0.0843   0.9392
  12.500   1.3765   0.03471   0.02837  -0.0590   0.0746   0.9449
  12.750   1.3849   0.03612   0.02979  -0.0577   0.0660   0.9536
  13.000   1.3944   0.03746   0.03116  -0.0568   0.0582   0.9910
  13.250   1.4039   0.03911   0.03281  -0.0560   0.0508   1.0000
  13.500   1.4123   0.04089   0.03458  -0.0553   0.0440   1.0000
  13.750   1.4207   0.04271   0.03640  -0.0546   0.0372   1.0000
  14.000   1.4275   0.04471   0.03840  -0.0539   0.0302   1.0000
  14.250   1.4302   0.04715   0.04081  -0.0530   0.0225   1.0000
  14.500   1.4312   0.04983   0.04349  -0.0521   0.0171   1.0000
  14.750   1.4338   0.05242   0.04613  -0.0515   0.0143   1.0000
  15.000   1.4363   0.05511   0.04891  -0.0509   0.0127   1.0000
  15.250   1.4398   0.05775   0.05162  -0.0505   0.0118   1.0000
  15.500   1.4410   0.06070   0.05466  -0.0502   0.0111   1.0000
  15.750   1.4370   0.06436   0.05841  -0.0499   0.0104   1.0000
  16.000   1.4392   0.06736   0.06155  -0.0499   0.0101   1.0000
  16.250   1.4404   0.07054   0.06483  -0.0500   0.0097   1.0000
  16.500   1.4402   0.07398   0.06838  -0.0503   0.0093   1.0000
  16.750   1.4389   0.07762   0.07213  -0.0507   0.0089   1.0000
  17.000   1.4352   0.08169   0.07630  -0.0514   0.0087   1.0000
  17.250   1.4305   0.08599   0.08071  -0.0522   0.0084   1.0000
  17.500   1.4231   0.09082   0.08565  -0.0533   0.0082   1.0000
  17.750   1.4113   0.09641   0.09137  -0.0548   0.0080   1.0000
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