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EPPLER 562 AIRFOIL (e562-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 562 AIRFOIL (e562-il)
Reynolds number: 100,000
Max Cl/Cd: 49.28 at α=9°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e562-il-100000.txt
Download as CSV file: xf-e562-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 562 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.3990   0.10904   0.10401  -0.0472   1.0000   0.0841
 -10.750  -0.3930   0.10560   0.10056  -0.0465   1.0000   0.0807
 -10.500  -0.5969   0.06661   0.06151  -0.0725   1.0000   0.0601
 -10.250  -0.6231   0.06267   0.05757  -0.0724   1.0000   0.0596
 -10.000  -0.6532   0.05935   0.05423  -0.0718   1.0000   0.0593
  -9.750  -0.6751   0.05550   0.05026  -0.0719   1.0000   0.0589
  -9.500  -0.6922   0.05175   0.04628  -0.0717   1.0000   0.0588
  -9.250  -0.7024   0.04815   0.04233  -0.0716   1.0000   0.0593
  -9.000  -0.7043   0.04475   0.03850  -0.0716   1.0000   0.0598
  -8.750  -0.6991   0.04161   0.03492  -0.0716   1.0000   0.0604
  -8.500  -0.6879   0.03831   0.03146  -0.0713   1.0000   0.0616
  -8.250  -0.6734   0.03619   0.02925  -0.0707   1.0000   0.0634
  -8.000  -0.6574   0.03451   0.02743  -0.0703   1.0000   0.0660
  -7.750  -0.6397   0.03287   0.02549  -0.0700   1.0000   0.0696
  -7.500  -0.6214   0.03094   0.02339  -0.0696   1.0000   0.0729
  -7.250  -0.6033   0.02966   0.02216  -0.0689   1.0000   0.0768
  -7.000  -0.5832   0.02856   0.02081  -0.0686   1.0000   0.0827
  -6.750  -0.5645   0.02729   0.01972  -0.0682   1.0000   0.0900
  -6.500  -0.5442   0.02610   0.01853  -0.0680   1.0000   0.0998
  -6.250  -0.5091   0.02480   0.01731  -0.0708   0.9965   0.1247
  -6.000  -0.4624   0.02365   0.01647  -0.0760   0.9896   0.1830
  -5.750  -0.4158   0.02381   0.01675  -0.0806   0.9817   0.2325
  -5.500  -0.3711   0.02442   0.01737  -0.0842   0.9730   0.2688
  -5.250  -0.3313   0.02500   0.01798  -0.0866   0.9630   0.2975
  -5.000  -0.2916   0.02533   0.01822  -0.0890   0.9533   0.3213
  -4.750  -0.2498   0.02552   0.01837  -0.0916   0.9448   0.3416
  -4.500  -0.2091   0.02567   0.01852  -0.0938   0.9358   0.3591
  -4.250  -0.1728   0.02564   0.01841  -0.0953   0.9254   0.3749
  -4.000  -0.1251   0.02548   0.01818  -0.0988   0.9194   0.3912
  -3.750  -0.0913   0.02527   0.01785  -0.1000   0.9079   0.4056
  -3.500  -0.0557   0.02516   0.01778  -0.1010   0.8982   0.4174
  -3.250  -0.0117   0.02482   0.01740  -0.1036   0.8911   0.4315
  -3.000   0.0228   0.02454   0.01706  -0.1047   0.8806   0.4443
  -2.750   0.0705   0.02396   0.01638  -0.1080   0.8750   0.4588
  -2.500   0.1061   0.02358   0.01588  -0.1094   0.8646   0.4719
  -2.250   0.1538   0.02296   0.01528  -0.1123   0.8595   0.4841
  -2.000   0.1906   0.02255   0.01483  -0.1136   0.8495   0.4955
  -1.750   0.2413   0.02188   0.01409  -0.1174   0.8438   0.5096
  -1.500   0.2793   0.02148   0.01361  -0.1191   0.8333   0.5228
  -1.250   0.3274   0.02088   0.01299  -0.1222   0.8266   0.5359
  -1.000   0.3600   0.02061   0.01273  -0.1227   0.8144   0.5471
  -0.750   0.3995   0.02023   0.01229  -0.1245   0.8042   0.5603
  -0.500   0.4403   0.01986   0.01184  -0.1265   0.7940   0.5741
  -0.250   0.4703   0.01974   0.01170  -0.1266   0.7807   0.5867
   0.000   0.5008   0.01961   0.01158  -0.1267   0.7682   0.5985
   0.250   0.5349   0.01944   0.01136  -0.1275   0.7570   0.6117
   0.500   0.5671   0.01933   0.01119  -0.1279   0.7450   0.6255
   0.750   0.5936   0.01936   0.01120  -0.1275   0.7317   0.6393
   1.000   0.6207   0.01938   0.01123  -0.1271   0.7193   0.6532
   1.250   0.6502   0.01935   0.01118  -0.1270   0.7083   0.6675
   1.500   0.6776   0.01936   0.01119  -0.1266   0.6966   0.6824
   1.750   0.7012   0.01948   0.01135  -0.1256   0.6843   0.6979
   2.000   0.7276   0.01955   0.01143  -0.1251   0.6734   0.7148
   2.250   0.7562   0.01957   0.01143  -0.1248   0.6632   0.7337
   2.500   0.7775   0.01974   0.01168  -0.1235   0.6514   0.7535
   2.750   0.8012   0.01982   0.01181  -0.1223   0.6414   0.7744
   3.000   0.8256   0.01988   0.01189  -0.1212   0.6315   0.8002
   3.250   0.8426   0.02001   0.01214  -0.1188   0.6210   0.8289
   3.500   0.8648   0.01991   0.01206  -0.1170   0.6129   0.8685
   3.750   0.8804   0.01983   0.01220  -0.1143   0.6021   0.9442
   4.000   0.9235   0.02015   0.01241  -0.1183   0.5913   1.0000
   4.250   0.9600   0.02046   0.01257  -0.1204   0.5819   1.0000
   4.500   0.9855   0.02096   0.01308  -0.1204   0.5712   1.0000
   4.750   1.0173   0.02131   0.01331  -0.1212   0.5626   1.0000
   5.000   1.0417   0.02177   0.01379  -0.1208   0.5524   1.0000
   5.250   1.0682   0.02224   0.01424  -0.1207   0.5434   1.0000
   5.500   1.0961   0.02262   0.01458  -0.1207   0.5344   1.0000
   5.750   1.1189   0.02318   0.01520  -0.1200   0.5249   1.0000
   6.000   1.1497   0.02349   0.01542  -0.1204   0.5166   1.0000
   6.250   1.1691   0.02413   0.01619  -0.1191   0.5067   1.0000
   6.500   1.2007   0.02445   0.01641  -0.1196   0.4988   1.0000
   6.750   1.2188   0.02508   0.01719  -0.1181   0.4887   1.0000
   7.000   1.2453   0.02554   0.01763  -0.1178   0.4802   1.0000
   7.250   1.2683   0.02601   0.01817  -0.1170   0.4707   1.0000
   7.500   1.2899   0.02659   0.01883  -0.1160   0.4614   1.0000
   7.750   1.3188   0.02688   0.01907  -0.1160   0.4524   1.0000
   8.000   1.3351   0.02755   0.01991  -0.1141   0.4422   1.0000
   8.250   1.3633   0.02787   0.02018  -0.1141   0.4332   1.0000
   8.500   1.3816   0.02837   0.02080  -0.1124   0.4227   1.0000
   8.750   1.4010   0.02892   0.02144  -0.1111   0.4127   1.0000
   9.000   1.4321   0.02906   0.02147  -0.1113   0.4029   1.0000
   9.250   1.4425   0.02970   0.02234  -0.1085   0.3918   1.0000
   9.500   1.4611   0.03016   0.02286  -0.1070   0.3811   1.0000
   9.750   1.4873   0.03032   0.02295  -0.1065   0.3703   1.0000
  10.000   1.4983   0.03084   0.02364  -0.1037   0.3588   1.0000
  10.250   1.5107   0.03138   0.02429  -0.1013   0.3474   1.0000
  10.500   1.5276   0.03172   0.02464  -0.0994   0.3359   1.0000
  10.750   1.5464   0.03196   0.02482  -0.0978   0.3239   1.0000
  11.000   1.5480   0.03264   0.02568  -0.0938   0.3121   1.0000
  11.250   1.5506   0.03328   0.02644  -0.0900   0.3006   1.0000
  11.500   1.5554   0.03386   0.02704  -0.0865   0.2889   1.0000
  11.750   1.5604   0.03447   0.02761  -0.0832   0.2768   1.0000
  12.000   1.5558   0.03547   0.02873  -0.0789   0.2650   1.0000
  12.250   1.5504   0.03673   0.03010  -0.0750   0.2530   1.0000
  12.500   1.5460   0.03811   0.03153  -0.0715   0.2409   1.0000
  12.750   1.5414   0.03968   0.03310  -0.0684   0.2287   1.0000
  13.000   1.5364   0.04145   0.03484  -0.0657   0.2164   1.0000
  13.250   1.5278   0.04368   0.03713  -0.0631   0.2044   1.0000
  13.500   1.5174   0.04635   0.03989  -0.0609   0.1926   1.0000
  13.750   1.5083   0.04919   0.04277  -0.0593   0.1811   1.0000
  14.000   1.4998   0.05218   0.04575  -0.0579   0.1701   1.0000
  14.250   1.4931   0.05519   0.04866  -0.0569   0.1593   1.0000
  14.500   1.4808   0.05901   0.05262  -0.0564   0.1495   1.0000
  14.750   1.4718   0.06274   0.05639  -0.0560   0.1399   1.0000
  15.000   1.4661   0.06619   0.05975  -0.0558   0.1306   1.0000
  15.250   1.4555   0.07043   0.06411  -0.0561   0.1225   1.0000
  15.500   1.4488   0.07441   0.06811  -0.0563   0.1144   1.0000
  15.750   1.4493   0.07741   0.07092  -0.0562   0.1057   1.0000
  16.000   1.4354   0.08267   0.07648  -0.0574   0.1001   1.0000
  16.250   1.4385   0.08549   0.07912  -0.0573   0.0925   1.0000
  16.500   1.4256   0.09089   0.08480  -0.0589   0.0879   1.0000
  16.750   1.4333   0.09310   0.08679  -0.0586   0.0809   1.0000
  17.000   1.4189   0.09895   0.09298  -0.0607   0.0777   1.0000
  17.250   1.4140   0.10331   0.09746  -0.0621   0.0735   1.0000
  17.500   1.4199   0.10598   0.10005  -0.0622   0.0687   1.0000
  17.750   1.4055   0.11212   0.10648  -0.0649   0.0664   1.0000
  18.000   1.3967   0.11740   0.11195  -0.0672   0.0638   1.0000
  18.250   1.4139   0.11813   0.11244  -0.0662   0.0591   1.0000
  18.500   1.3954   0.12521   0.11984  -0.0700   0.0582   1.0000
  18.750   1.3763   0.13269   0.12762  -0.0743   0.0573   1.0000
  19.000   1.3547   0.14093   0.13613  -0.0794   0.0567   1.0000
  19.250   1.3272   0.15078   0.14626  -0.0858   0.0567   1.0000
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