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EPPLER 560 AIRFOIL (e560-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER 560 AIRFOIL (e560-il)
Reynolds number: 1,000,000
Max Cl/Cd: 123.55 at α=8.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e560-il-1000000-n5.txt
Download as CSV file: xf-e560-il-1000000-n5.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 =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.750  -0.7479   0.08908   0.08595  -0.0610   1.0000   0.0108
 -15.500  -0.7562   0.08475   0.08158  -0.0628   1.0000   0.0108
 -15.250  -0.7663   0.08027   0.07704  -0.0647   1.0000   0.0108
 -15.000  -0.7704   0.07560   0.07231  -0.0679   0.9996   0.0108
 -14.750  -0.7687   0.07015   0.06678  -0.0737   0.9982   0.0109
 -14.500  -0.7686   0.06481   0.06135  -0.0793   0.9966   0.0110
 -14.250  -0.7700   0.05962   0.05608  -0.0847   0.9952   0.0110
 -14.000  -0.7731   0.05448   0.05085  -0.0901   0.9940   0.0111
 -13.750  -0.7804   0.04958   0.04586  -0.0944   0.9919   0.0111
 -13.500  -0.7893   0.04438   0.04057  -0.0993   0.9888   0.0111
 -13.250  -0.7937   0.03902   0.03510  -0.1055   0.9857   0.0111
 -13.000  -0.7897   0.03389   0.02985  -0.1130   0.9832   0.0112
 -12.750  -0.8008   0.02886   0.02471  -0.1170   0.9745   0.0112
 -12.500  -0.7740   0.02436   0.02005  -0.1267   0.9720   0.0113
 -12.250  -0.7629   0.02186   0.01742  -0.1293   0.9635   0.0114
 -11.750  -0.7211   0.01882   0.01419  -0.1324   0.9512   0.0118
 -11.500  -0.6935   0.01773   0.01304  -0.1341   0.9468   0.0120
 -11.250  -0.6706   0.01689   0.01213  -0.1343   0.9388   0.0123
 -10.750  -0.6048   0.01532   0.01045  -0.1382   0.9282   0.0128
 -10.500  -0.5648   0.01460   0.00967  -0.1413   0.9223   0.0132
 -10.250  -0.5194   0.01394   0.00894  -0.1456   0.9164   0.0135
 -10.000  -0.4683   0.01336   0.00828  -0.1509   0.9079   0.0140
  -9.750  -0.4146   0.01282   0.00764  -0.1568   0.8957   0.0144
  -9.500  -0.3739   0.01233   0.00702  -0.1600   0.8748   0.0152
  -9.250  -0.3439   0.01203   0.00658  -0.1608   0.8512   0.0157
  -9.000  -0.3180   0.01177   0.00620  -0.1607   0.8293   0.0164
  -8.750  -0.2931   0.01156   0.00587  -0.1602   0.8083   0.0171
  -8.500  -0.2685   0.01135   0.00555  -0.1597   0.7890   0.0181
  -8.250  -0.2436   0.01110   0.00521  -0.1593   0.7718   0.0199
  -7.750  -0.1931   0.01046   0.00449  -0.1587   0.7396   0.0342
  -7.500  -0.1673   0.01015   0.00416  -0.1586   0.7250   0.0453
  -7.250  -0.1409   0.00989   0.00389  -0.1584   0.7116   0.0551
  -7.000  -0.1144   0.00965   0.00363  -0.1583   0.6983   0.0666
  -6.750  -0.0877   0.00945   0.00341  -0.1582   0.6857   0.0776
  -6.500  -0.0605   0.00922   0.00319  -0.1582   0.6736   0.0910
  -6.250  -0.0331   0.00908   0.00302  -0.1581   0.6618   0.1010
  -6.000  -0.0058   0.00894   0.00286  -0.1580   0.6501   0.1113
  -5.750   0.0219   0.00880   0.00271  -0.1580   0.6388   0.1228
  -5.500   0.0497   0.00869   0.00259  -0.1579   0.6283   0.1335
  -5.250   0.0773   0.00862   0.00248  -0.1579   0.6174   0.1438
  -5.000   0.1053   0.00853   0.00238  -0.1579   0.6067   0.1544
  -4.750   0.1333   0.00845   0.00229  -0.1578   0.5974   0.1648
  -4.500   0.1612   0.00842   0.00222  -0.1578   0.5873   0.1737
  -4.250   0.1894   0.00835   0.00216  -0.1578   0.5774   0.1857
  -4.000   0.2172   0.00832   0.00210  -0.1577   0.5679   0.1950
  -3.750   0.2456   0.00830   0.00205  -0.1577   0.5593   0.2025
  -3.500   0.2735   0.00830   0.00201  -0.1576   0.5505   0.2091
  -3.250   0.3018   0.00829   0.00198  -0.1576   0.5414   0.2164
  -3.000   0.3297   0.00831   0.00195  -0.1575   0.5327   0.2219
  -2.750   0.3580   0.00830   0.00193  -0.1575   0.5245   0.2286
  -2.500   0.3859   0.00833   0.00192  -0.1573   0.5169   0.2346
  -2.250   0.4142   0.00833   0.00191  -0.1573   0.5088   0.2410
  -2.000   0.4419   0.00837   0.00191  -0.1572   0.5005   0.2478
  -1.750   0.4702   0.00839   0.00191  -0.1572   0.4934   0.2534
  -1.500   0.4980   0.00842   0.00193  -0.1571   0.4862   0.2604
  -1.250   0.5262   0.00845   0.00194  -0.1570   0.4798   0.2664
  -1.000   0.5540   0.00849   0.00196  -0.1569   0.4720   0.2721
  -0.750   0.5819   0.00853   0.00198  -0.1568   0.4656   0.2790
  -0.500   0.6099   0.00858   0.00201  -0.1567   0.4593   0.2848
  -0.250   0.6374   0.00863   0.00205  -0.1565   0.4529   0.2910
   0.000   0.6654   0.00868   0.00209  -0.1565   0.4472   0.2974
   0.250   0.6930   0.00873   0.00213  -0.1563   0.4406   0.3036
   0.500   0.7204   0.00880   0.00219  -0.1561   0.4345   0.3105
   0.750   0.7483   0.00885   0.00224  -0.1560   0.4296   0.3162
   1.000   0.7758   0.00891   0.00230  -0.1559   0.4237   0.3230
   1.250   0.8029   0.00900   0.00237  -0.1556   0.4179   0.3301
   1.500   0.8305   0.00906   0.00243  -0.1555   0.4127   0.3356
   1.750   0.8578   0.00913   0.00251  -0.1553   0.4075   0.3430
   2.000   0.8846   0.00923   0.00260  -0.1550   0.4024   0.3501
   2.250   0.9121   0.00929   0.00268  -0.1549   0.3980   0.3566
   2.500   0.9391   0.00937   0.00277  -0.1546   0.3925   0.3637
   2.750   0.9656   0.00948   0.00287  -0.1543   0.3874   0.3709
   3.000   0.9927   0.00956   0.00297  -0.1541   0.3835   0.3788
   3.250   1.0195   0.00964   0.00307  -0.1538   0.3788   0.3855
   3.500   1.0458   0.00975   0.00318  -0.1535   0.3736   0.3935
   3.750   1.0720   0.00987   0.00330  -0.1531   0.3692   0.4022
   4.000   1.0988   0.00994   0.00342  -0.1528   0.3652   0.4105
   4.250   1.1249   0.01006   0.00354  -0.1524   0.3602   0.4191
   4.500   1.1504   0.01019   0.00369  -0.1520   0.3553   0.4290
   5.000   1.2024   0.01040   0.00396  -0.1512   0.3466   0.4508
   5.250   1.2275   0.01053   0.00412  -0.1506   0.3415   0.4622
   5.500   1.2525   0.01067   0.00429  -0.1501   0.3367   0.4765
   5.750   1.2778   0.01078   0.00444  -0.1496   0.3322   0.4922
   6.250   1.3251   0.01108   0.00481  -0.1480   0.3215   0.5287
   6.500   1.3493   0.01119   0.00499  -0.1473   0.3164   0.5522
   6.750   1.3723   0.01135   0.00520  -0.1464   0.3103   0.5764
   7.000   1.3952   0.01152   0.00543  -0.1455   0.3046   0.6083
   7.250   1.4184   0.01166   0.00566  -0.1446   0.2983   0.6450
   7.500   1.4399   0.01187   0.00594  -0.1435   0.2913   0.6873
   7.750   1.4628   0.01199   0.00620  -0.1426   0.2857   0.7436
   8.000   1.4832   0.01212   0.00651  -0.1412   0.2786   0.8253
   8.250   1.4974   0.01212   0.00672  -0.1384   0.2730   1.0000
   8.500   1.5183   0.01241   0.00699  -0.1372   0.2649   1.0000
   8.750   1.5377   0.01275   0.00730  -0.1358   0.2564   1.0000
   9.000   1.5551   0.01319   0.00768  -0.1340   0.2441   1.0000
   9.250   1.5717   0.01368   0.00810  -0.1322   0.2303   1.0000
   9.500   1.5878   0.01418   0.00854  -0.1303   0.2169   1.0000
   9.750   1.6014   0.01479   0.00907  -0.1280   0.2019   1.0000
  10.000   1.6137   0.01547   0.00967  -0.1256   0.1864   1.0000
  10.250   1.6240   0.01624   0.01036  -0.1229   0.1702   1.0000
  10.500   1.6347   0.01700   0.01106  -0.1204   0.1569   1.0000
  10.750   1.6446   0.01781   0.01182  -0.1178   0.1448   1.0000
  11.000   1.6533   0.01870   0.01266  -0.1152   0.1326   1.0000
  11.250   1.6615   0.01964   0.01356  -0.1126   0.1216   1.0000
  11.500   1.6697   0.02062   0.01451  -0.1101   0.1127   1.0000
  11.750   1.6743   0.02184   0.01569  -0.1074   0.1017   1.0000
  12.000   1.6775   0.02320   0.01701  -0.1046   0.0911   1.0000
  12.250   1.6817   0.02457   0.01837  -0.1022   0.0827   1.0000
  12.500   1.6858   0.02603   0.01982  -0.0999   0.0750   1.0000
  12.750   1.6890   0.02764   0.02142  -0.0978   0.0688   1.0000
  13.000   1.6905   0.02947   0.02324  -0.0957   0.0618   1.0000
  13.250   1.6921   0.03138   0.02517  -0.0938   0.0557   1.0000
  13.500   1.6914   0.03360   0.02740  -0.0921   0.0500   1.0000
  13.750   1.6918   0.03586   0.02968  -0.0906   0.0451   1.0000
  14.000   1.6924   0.03820   0.03205  -0.0894   0.0415   1.0000
  14.250   1.6917   0.04078   0.03467  -0.0883   0.0379   1.0000
  14.500   1.6914   0.04344   0.03737  -0.0875   0.0350   1.0000
  14.750   1.6910   0.04622   0.04020  -0.0868   0.0324   1.0000
  15.000   1.6883   0.04933   0.04336  -0.0863   0.0298   1.0000
  15.250   1.6858   0.05256   0.04665  -0.0860   0.0273   1.0000
  15.500   1.6815   0.05613   0.05027  -0.0858   0.0249   1.0000
  15.750   1.6781   0.05967   0.05387  -0.0858   0.0228   1.0000
  16.000   1.6727   0.06358   0.05784  -0.0860   0.0208   1.0000
  16.250   1.6673   0.06760   0.06193  -0.0864   0.0185   1.0000
  16.500   1.6606   0.07193   0.06632  -0.0870   0.0166   1.0000
  16.750   1.6519   0.07662   0.07108  -0.0878   0.0143   1.0000
  17.000   1.6449   0.08120   0.07572  -0.0887   0.0124   1.0000
  17.250   1.6361   0.08613   0.08072  -0.0898   0.0106   1.0000
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