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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 100,000
Max Cl/Cd: 45.65 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e560-il-100000.txt
Download as CSV file: xf-e560-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 560 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.5980   0.06520   0.06015  -0.0747   1.0000   0.0669
 -10.500  -0.6339   0.06105   0.05602  -0.0742   1.0000   0.0665
 -10.250  -0.6682   0.05790   0.05288  -0.0729   1.0000   0.0659
 -10.000  -0.6989   0.05326   0.04813  -0.0753   1.0000   0.0655
  -9.750  -0.7184   0.04898   0.04355  -0.0772   1.0000   0.0656
  -9.500  -0.7257   0.04504   0.03919  -0.0791   1.0000   0.0664
  -9.250  -0.7211   0.04204   0.03599  -0.0796   1.0000   0.0679
  -9.000  -0.7102   0.04054   0.03454  -0.0789   1.0000   0.0699
  -8.750  -0.6981   0.03863   0.03248  -0.0792   1.0000   0.0723
  -8.500  -0.6835   0.03638   0.02992  -0.0800   1.0000   0.0751
  -8.250  -0.6496   0.03410   0.02750  -0.0835   0.9956   0.0802
  -8.000  -0.6065   0.03219   0.02536  -0.0885   0.9885   0.0901
  -7.750  -0.5626   0.03102   0.02433  -0.0933   0.9816   0.1068
  -7.500  -0.5188   0.02990   0.02314  -0.0980   0.9736   0.1308
  -7.250  -0.4781   0.02983   0.02314  -0.1013   0.9646   0.1507
  -7.000  -0.4354   0.02978   0.02289  -0.1051   0.9560   0.1711
  -6.750  -0.3917   0.03054   0.02382  -0.1081   0.9479   0.1901
  -6.500  -0.3562   0.03088   0.02418  -0.1095   0.9375   0.2055
  -6.250  -0.3160   0.03057   0.02374  -0.1122   0.9289   0.2200
  -6.000  -0.2745   0.03050   0.02367  -0.1145   0.9210   0.2331
  -5.750  -0.2410   0.03052   0.02377  -0.1152   0.9109   0.2432
  -5.500  -0.1949   0.03004   0.02318  -0.1185   0.9048   0.2568
  -5.250  -0.1613   0.02948   0.02244  -0.1200   0.8942   0.2696
  -5.000  -0.1127   0.02888   0.02164  -0.1237   0.8889   0.2842
  -4.750  -0.0838   0.02897   0.02191  -0.1232   0.8780   0.2918
  -4.500  -0.0353   0.02817   0.02096  -0.1267   0.8731   0.3053
  -4.250   0.0005   0.02752   0.02008  -0.1285   0.8632   0.3181
  -4.000   0.0451   0.02710   0.01976  -0.1305   0.8579   0.3280
  -3.750   0.1007   0.02617   0.01871  -0.1352   0.8549   0.3412
  -3.500   0.1328   0.02562   0.01795  -0.1363   0.8431   0.3530
  -3.250   0.1853   0.02494   0.01727  -0.1401   0.8389   0.3645
  -3.000   0.2163   0.02452   0.01677  -0.1406   0.8271   0.3742
  -2.750   0.2700   0.02364   0.01569  -0.1451   0.8218   0.3880
  -2.500   0.2979   0.02346   0.01555  -0.1447   0.8092   0.3962
  -2.250   0.3356   0.02298   0.01493  -0.1465   0.7991   0.4076
  -2.000   0.3765   0.02253   0.01435  -0.1486   0.7897   0.4193
  -1.750   0.4046   0.02235   0.01416  -0.1484   0.7774   0.4280
  -1.500   0.4412   0.02202   0.01367  -0.1499   0.7673   0.4402
  -1.250   0.4730   0.02183   0.01345  -0.1503   0.7564   0.4496
  -1.000   0.5004   0.02173   0.01329  -0.1502   0.7444   0.4600
  -0.750   0.5344   0.02157   0.01300  -0.1511   0.7345   0.4720
  -0.500   0.5620   0.02149   0.01292  -0.1508   0.7234   0.4814
  -0.250   0.5891   0.02150   0.01286  -0.1507   0.7123   0.4930
   0.000   0.6239   0.02136   0.01262  -0.1516   0.7037   0.5055
   0.250   0.6457   0.02146   0.01277  -0.1505   0.6919   0.5153
   0.500   0.6751   0.02148   0.01272  -0.1506   0.6826   0.5281
   0.750   0.7033   0.02152   0.01272  -0.1506   0.6728   0.5415
   1.000   0.7278   0.02164   0.01289  -0.1499   0.6631   0.5531
   1.250   0.7579   0.02163   0.01284  -0.1500   0.6547   0.5671
   1.500   0.7808   0.02185   0.01311  -0.1492   0.6450   0.5812
   1.750   0.8116   0.02186   0.01307  -0.1495   0.6373   0.5973
   2.000   0.8334   0.02213   0.01342  -0.1484   0.6278   0.6132
   2.250   0.8635   0.02216   0.01344  -0.1485   0.6205   0.6316
   2.500   0.8841   0.02247   0.01387  -0.1472   0.6116   0.6500
   2.750   0.9123   0.02254   0.01397  -0.1470   0.6045   0.6725
   3.000   0.9340   0.02284   0.01438  -0.1459   0.5964   0.6973
   3.250   0.9586   0.02296   0.01458  -0.1450   0.5891   0.7266
   3.500   0.9814   0.02314   0.01487  -0.1438   0.5825   0.7634
   3.750   0.9953   0.02332   0.01528  -0.1409   0.5749   0.8102
   4.000   1.0111   0.02293   0.01505  -0.1375   0.5697   0.9318
   4.250   1.0418   0.02360   0.01568  -0.1393   0.5610   1.0000
   4.500   1.0755   0.02397   0.01591  -0.1407   0.5546   1.0000
   4.750   1.1008   0.02460   0.01651  -0.1406   0.5477   1.0000
   5.000   1.1254   0.02515   0.01704  -0.1402   0.5404   1.0000
   5.250   1.1610   0.02543   0.01717  -0.1415   0.5353   1.0000
   5.500   1.1739   0.02638   0.01827  -0.1395   0.5273   1.0000
   5.750   1.2037   0.02675   0.01858  -0.1398   0.5213   1.0000
   6.000   1.2273   0.02743   0.01929  -0.1393   0.5152   1.0000
   6.250   1.2460   0.02820   0.02014  -0.1380   0.5081   1.0000
   6.500   1.2803   0.02844   0.02028  -0.1389   0.5028   1.0000
   6.750   1.2923   0.02952   0.02151  -0.1368   0.4957   1.0000
   7.000   1.3169   0.03005   0.02207  -0.1363   0.4894   1.0000
   7.250   1.3505   0.03038   0.02233  -0.1371   0.4843   1.0000
   7.500   1.3560   0.03164   0.02380  -0.1340   0.4766   1.0000
   7.750   1.3873   0.03191   0.02405  -0.1345   0.4709   1.0000
   8.000   1.4033   0.03287   0.02511  -0.1328   0.4645   1.0000
   8.250   1.4193   0.03369   0.02603  -0.1312   0.4576   1.0000
   8.500   1.4613   0.03357   0.02580  -0.1331   0.4523   1.0000
   8.750   1.4566   0.03523   0.02774  -0.1286   0.4446   1.0000
   9.000   1.4874   0.03536   0.02786  -0.1289   0.4383   1.0000
   9.250   1.5027   0.03627   0.02886  -0.1272   0.4317   1.0000
   9.500   1.5148   0.03711   0.02984  -0.1249   0.4244   1.0000
   9.750   1.5584   0.03675   0.02937  -0.1268   0.4182   1.0000
  10.000   1.5460   0.03855   0.03146  -0.1215   0.4104   1.0000
  10.250   1.5949   0.03776   0.03054  -0.1239   0.4035   1.0000
  10.500   1.5809   0.03962   0.03267  -0.1184   0.3961   1.0000
  10.750   1.6186   0.03913   0.03214  -0.1193   0.3885   1.0000
  11.000   1.6160   0.04047   0.03365  -0.1152   0.3813   1.0000
  11.250   1.6396   0.04044   0.03365  -0.1143   0.3733   1.0000
  11.500   1.6452   0.04123   0.03453  -0.1111   0.3660   1.0000
  11.750   1.6532   0.04173   0.03512  -0.1082   0.3581   1.0000
  12.000   1.6661   0.04215   0.03559  -0.1061   0.3503   1.0000
  12.250   1.6664   0.04296   0.03650  -0.1025   0.3423   1.0000
  12.500   1.6774   0.04343   0.03701  -0.1002   0.3341   1.0000
  12.750   1.6788   0.04422   0.03789  -0.0970   0.3258   1.0000
  13.000   1.6797   0.04530   0.03905  -0.0941   0.3177   1.0000
  13.250   1.6989   0.04513   0.03886  -0.0927   0.3081   1.0000
  13.500   1.6742   0.04798   0.04193  -0.0883   0.3010   1.0000
  13.750   1.7046   0.04712   0.04093  -0.0878   0.2903   1.0000
  14.000   1.6633   0.05160   0.04572  -0.0834   0.2838   1.0000
  14.250   1.6812   0.05163   0.04568  -0.0822   0.2734   1.0000
  14.500   1.6557   0.05551   0.04975  -0.0797   0.2655   1.0000
  14.750   1.6541   0.05751   0.05178  -0.0783   0.2561   1.0000
  15.000   1.6697   0.05783   0.05198  -0.0772   0.2448   1.0000
  15.250   1.6300   0.06412   0.05856  -0.0761   0.2378   1.0000
  15.500   1.6347   0.06580   0.06019  -0.0753   0.2274   1.0000
  15.750   1.6242   0.06936   0.06381  -0.0748   0.2179   1.0000
  16.000   1.6056   0.07429   0.06885  -0.0749   0.2093   1.0000
  16.250   1.6110   0.07617   0.07065  -0.0745   0.1988   1.0000
  16.500   1.5911   0.08165   0.07627  -0.0752   0.1904   1.0000
  16.750   1.5832   0.08567   0.08032  -0.0756   0.1816   1.0000
  17.000   1.5912   0.08736   0.08185  -0.0753   0.1710   1.0000
  17.250   1.5637   0.09461   0.08935  -0.0774   0.1645   1.0000
  17.500   1.5649   0.09742   0.09207  -0.0777   0.1552   1.0000
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