Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)
Reynolds number: 1,000,000
Max Cl/Cd: 100.97 at α=-0.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-ec863914-il-1000000-n5.txt
Download as CSV file: xf-ec863914-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER EC 86(-3)-914 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
  ------ -------- --------- --------- -------- -------- --------
 -14.750  -0.0297   0.10299   0.10100  -0.1380   0.9570   0.0040
 -14.500  -0.1390   0.10975   0.10762  -0.1366   0.9676   0.0036
 -14.250  -0.1511   0.10068   0.09850  -0.1407   0.9666   0.0036
 -14.000  -0.1500   0.09545   0.09323  -0.1439   0.9658   0.0036
 -13.750  -0.1637   0.08658   0.08428  -0.1495   0.9649   0.0036
 -13.500  -0.1769   0.07819   0.07578  -0.1558   0.9640   0.0036
 -13.250  -0.1869   0.07073   0.06822  -0.1623   0.9630   0.0036
 -13.000  -0.1922   0.06437   0.06175  -0.1684   0.9618   0.0036
 -12.750  -0.2073   0.05833   0.05559  -0.1730   0.9593   0.0036
 -12.500  -0.2070   0.05511   0.05233  -0.1749   0.9572   0.0036
 -12.250  -0.2132   0.05079   0.04790  -0.1786   0.9547   0.0036
 -12.000  -0.2289   0.04538   0.04230  -0.1836   0.9518   0.0036
 -11.750  -0.2280   0.04238   0.03919  -0.1866   0.9498   0.0036
 -11.500  -0.2442   0.03931   0.03597  -0.1868   0.9462   0.0036
 -11.250  -0.2523   0.03706   0.03360  -0.1867   0.9427   0.0036
 -11.000  -0.2569   0.03487   0.03128  -0.1867   0.9396   0.0036
 -10.750  -0.2584   0.03290   0.02917  -0.1867   0.9367   0.0036
 -10.500  -0.2672   0.03129   0.02745  -0.1842   0.9331   0.0036
 -10.250  -0.2702   0.03003   0.02611  -0.1816   0.9297   0.0036
 -10.000  -0.2727   0.02837   0.02427  -0.1805   0.9265   0.0036
  -9.750  -0.2640   0.02672   0.02242  -0.1805   0.9244   0.0036
  -9.500  -0.2457   0.02329   0.01900  -0.1791   0.9239   0.0033
  -9.000  -0.2207   0.02100   0.01644  -0.1775   0.9196   0.0034
  -8.000  -0.1460   0.01639   0.01154  -0.1752   0.9137   0.0043
  -7.500  -0.0969   0.01486   0.00988  -0.1761   0.9116   0.0064
  -7.250  -0.0705   0.01418   0.00914  -0.1765   0.9108   0.0063
  -7.000  -0.0454   0.01369   0.00860  -0.1766   0.9098   0.0061
  -6.750  -0.0212   0.01356   0.00842  -0.1761   0.9084   0.0058
  -6.500   0.0029   0.01316   0.00800  -0.1759   0.9068   0.0058
  -6.000   0.0566   0.01166   0.00647  -0.1774   0.9041   0.0060
  -5.750   0.0865   0.01129   0.00607  -0.1783   0.9031   0.0059
  -5.500   0.1181   0.01085   0.00562  -0.1796   0.9020   0.0055
  -5.250   0.1513   0.01032   0.00503  -0.1812   0.9008   0.0052
  -5.000   0.1847   0.00990   0.00457  -0.1828   0.8996   0.0050
  -4.750   0.2165   0.00958   0.00423  -0.1839   0.8982   0.0049
  -4.500   0.2426   0.00936   0.00400  -0.1838   0.8959   0.0048
  -4.250   0.2717   0.00915   0.00377  -0.1843   0.8940   0.0046
  -4.000   0.3022   0.00894   0.00354  -0.1851   0.8923   0.0045
  -3.750   0.3338   0.00874   0.00332  -0.1860   0.8906   0.0044
  -3.500   0.3668   0.00852   0.00308  -0.1872   0.8885   0.0044
  -3.250   0.3967   0.00835   0.00289  -0.1878   0.8853   0.0043
  -3.000   0.4236   0.00821   0.00274  -0.1877   0.8804   0.0044
  -2.750   0.4570   0.00800   0.00249  -0.1889   0.8758   0.0044
  -2.500   0.4811   0.00790   0.00239  -0.1881   0.8685   0.0045
  -2.250   0.5133   0.00777   0.00223  -0.1891   0.8638   0.0047
  -2.000   0.5389   0.00769   0.00216  -0.1887   0.8556   0.0052
  -1.750   0.5789   0.00691   0.00188  -0.1922   0.8423   0.1941
  -1.500   0.6154   0.00647   0.00174  -0.1947   0.8248   0.2963
  -1.250   0.6439   0.00641   0.00165  -0.1950   0.7953   0.3283
  -1.000   0.6645   0.00660   0.00167  -0.1936   0.7482   0.3588
  -0.750   0.6841   0.00682   0.00179  -0.1920   0.7102   0.3943
  -0.500   0.7052   0.00700   0.00191  -0.1908   0.6785   0.4318
  -0.250   0.7260   0.00719   0.00205  -0.1896   0.6456   0.4688
   0.000   0.7450   0.00740   0.00221  -0.1881   0.6071   0.5177
   0.250   0.7644   0.00768   0.00246  -0.1866   0.5665   0.5770
   0.500   0.7824   0.00807   0.00272  -0.1847   0.5277   0.6036
   0.750   0.8027   0.00842   0.00295  -0.1833   0.4958   0.6175
   1.000   0.8240   0.00876   0.00315  -0.1821   0.4667   0.6275
   1.250   0.8458   0.00910   0.00337  -0.1810   0.4383   0.6349
   1.500   0.8681   0.00942   0.00357  -0.1801   0.4119   0.6401
   1.750   0.8906   0.00974   0.00379  -0.1791   0.3873   0.6447
   2.000   0.9130   0.01008   0.00402  -0.1782   0.3628   0.6503
   2.250   0.9357   0.01041   0.00424  -0.1773   0.3393   0.6565
   2.500   0.9583   0.01074   0.00449  -0.1764   0.3184   0.6620
   2.750   0.9818   0.01104   0.00471  -0.1757   0.3021   0.6666
   3.000   1.0056   0.01132   0.00493  -0.1751   0.2875   0.6701
   3.250   1.0290   0.01160   0.00517  -0.1743   0.2738   0.6738
   3.500   1.0525   0.01188   0.00541  -0.1736   0.2614   0.6779
   3.750   1.0760   0.01216   0.00565  -0.1729   0.2504   0.6814
   4.000   1.0996   0.01244   0.00589  -0.1722   0.2401   0.6842
   4.500   1.1463   0.01300   0.00642  -0.1708   0.2206   0.6887
   4.750   1.1697   0.01329   0.00669  -0.1701   0.2123   0.6902
   5.000   1.1932   0.01357   0.00695  -0.1695   0.2052   0.6913
   5.250   1.2160   0.01389   0.00725  -0.1687   0.1963   0.6925
   5.500   1.2380   0.01426   0.00757  -0.1678   0.1853   0.6935
   5.750   1.2608   0.01458   0.00787  -0.1671   0.1769   0.6946
   6.000   1.2832   0.01493   0.00820  -0.1662   0.1683   0.6955
   6.250   1.3048   0.01534   0.00855  -0.1653   0.1577   0.6965
   6.500   1.3269   0.01572   0.00891  -0.1645   0.1477   0.6974
   6.750   1.3468   0.01626   0.00935  -0.1633   0.1306   0.6982
   7.000   1.3530   0.01790   0.01051  -0.1601   0.0583   0.6992
   7.250   1.3595   0.01967   0.01196  -0.1567   0.0052   0.7003
   7.500   1.3798   0.02018   0.01250  -0.1557   0.0035   0.7014
   7.750   1.4002   0.02069   0.01305  -0.1546   0.0030   0.7025
   8.000   1.4197   0.02126   0.01368  -0.1534   0.0026   0.7035
   8.250   1.4385   0.02190   0.01437  -0.1521   0.0022   0.7045
   8.500   1.4569   0.02255   0.01508  -0.1508   0.0020   0.7056
   8.750   1.4756   0.02317   0.01575  -0.1495   0.0019   0.7067
   9.000   1.4934   0.02386   0.01649  -0.1481   0.0018   0.7078
   9.250   1.5105   0.02459   0.01728  -0.1467   0.0016   0.7089
   9.500   1.5275   0.02534   0.01808  -0.1452   0.0015   0.7100
   9.750   1.5437   0.02614   0.01894  -0.1437   0.0014   0.7110
  10.000   1.5596   0.02695   0.01980  -0.1422   0.0012   0.7121
  10.250   1.5744   0.02786   0.02077  -0.1405   0.0011   0.7130
  10.500   1.5872   0.02896   0.02195  -0.1387   0.0010   0.7141
  10.750   1.5973   0.03030   0.02340  -0.1365   0.0009   0.7152
  11.000   1.6076   0.03159   0.02479  -0.1344   0.0009   0.7163
  11.250   1.6198   0.03274   0.02601  -0.1326   0.0009   0.7176
  11.500   1.6305   0.03401   0.02737  -0.1307   0.0009   0.7189
  11.750   1.6406   0.03535   0.02880  -0.1288   0.0008   0.7203
  12.000   1.6505   0.03672   0.03024  -0.1270   0.0008   0.7216
  12.250   1.6579   0.03833   0.03195  -0.1250   0.0008   0.7229
  12.500   1.6637   0.04014   0.03387  -0.1229   0.0008   0.7241
  12.750   1.6713   0.04181   0.03564  -0.1212   0.0007   0.7253
  13.000   1.6770   0.04373   0.03765  -0.1194   0.0007   0.7265
  13.250   1.6790   0.04605   0.04009  -0.1174   0.0007   0.7275
  13.500   1.6840   0.04815   0.04228  -0.1159   0.0006   0.7287
  13.750   1.6856   0.05071   0.04495  -0.1143   0.0006   0.7299
  14.000   1.6877   0.05330   0.04766  -0.1129   0.0006   0.7311
  14.250   1.6871   0.05630   0.05077  -0.1117   0.0005   0.7324
  14.500   1.6846   0.05964   0.05425  -0.1106   0.0005   0.7336
  14.750   1.6813   0.06326   0.05798  -0.1099   0.0005   0.7348
  15.000   1.6821   0.06645   0.06127  -0.1095   0.0005   0.7362
  15.250   1.6731   0.07118   0.06616  -0.1093   0.0005   0.7374
  15.500   1.6685   0.07545   0.07055  -0.1095   0.0005   0.7386
  15.750   1.6593   0.08063   0.07587  -0.1101   0.0005   0.7397
  16.000   1.6524   0.08562   0.08098  -0.1111   0.0004   0.7409
  16.250   1.6426   0.09131   0.08681  -0.1125   0.0004   0.7419
  16.500   1.6272   0.09824   0.09390  -0.1147   0.0004   0.7428
  17.000   1.5977   0.11250   0.10847  -0.1204   0.0004   0.7445
  17.250   1.5830   0.11988   0.11600  -0.1237   0.0004   0.7455
<< Back to EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)

Polar data table (+)

Polar graphs


<< Back to EPPLER EC 86(-3)-914 AIRFOIL (ec863914-il)