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EPPLER 376 AIRFOIL (e376-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: EPPLER 376 AIRFOIL (e376-il)
Reynolds number: 50,000
Max Cl/Cd: 19.35 at α=2.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-e376-il-50000.txt
Download as CSV file: xf-e376-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: EPPLER 376 AIRFOIL                              
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.2833   0.13294   0.12644  -0.0100   1.0000   0.0332
  -9.500  -0.2772   0.13273   0.12632  -0.0117   1.0000   0.0333
  -9.250  -0.2721   0.13313   0.12682  -0.0136   1.0000   0.0334
  -8.750  -0.2483   0.11991   0.11370  -0.0142   1.0000   0.0342
  -8.500  -0.2378   0.11436   0.10818  -0.0145   1.0000   0.0350
  -8.250  -0.2294   0.11092   0.10482  -0.0151   1.0000   0.0359
  -8.000  -0.2218   0.10824   0.10222  -0.0158   1.0000   0.0368
  -7.750  -0.2138   0.10585   0.09993  -0.0167   1.0000   0.0376
  -7.500  -0.2053   0.10351   0.09768  -0.0178   1.0000   0.0386
  -7.250  -0.1968   0.10139   0.09567  -0.0189   1.0000   0.0395
  -7.000  -0.1893   0.09940   0.09380  -0.0199   1.0000   0.0405
  -6.750  -0.1844   0.09779   0.09233  -0.0204   1.0000   0.0414
  -6.500  -0.1855   0.09679   0.09150  -0.0198   1.0000   0.0421
  -6.250  -0.1975   0.09679   0.09161  -0.0172   1.0000   0.0424
  -6.000  -0.2143   0.09723   0.09220  -0.0140   1.0000   0.0425
  -5.750  -0.2260   0.09727   0.09235  -0.0122   1.0000   0.0428
  -5.500  -0.2321   0.09697   0.09213  -0.0114   1.0000   0.0433
  -5.250  -0.2337   0.09650   0.09173  -0.0116   1.0000   0.0438
  -5.000  -0.1729   0.09623   0.09134  -0.0270   0.9876   0.0453
  -4.750  -0.1182   0.09386   0.08887  -0.0396   0.9750   0.0459
  -4.500  -0.1055   0.08592   0.08097  -0.0399   0.9673   0.0473
  -4.250  -0.0732   0.08164   0.07666  -0.0456   0.9563   0.0500
  -4.000  -0.0358   0.07865   0.07360  -0.0527   0.9450   0.0536
  -3.750   0.0247   0.07797   0.07275  -0.0650   0.9333   0.0575
  -3.500   0.0702   0.07448   0.06915  -0.0733   0.9233   0.0590
  -3.250   0.0955   0.06992   0.06458  -0.0764   0.9141   0.0619
  -3.000   0.1302   0.06749   0.06207  -0.0817   0.9038   0.0659
  -2.500   0.2291   0.06252   0.05687  -0.0976   0.8857   0.0733
  -2.250   0.2581   0.06044   0.05473  -0.1010   0.8758   0.0781
  -2.000   0.3232   0.05945   0.05347  -0.1110   0.8679   0.0840
  -1.750   0.3431   0.05642   0.05043  -0.1123   0.8583   0.0883
  -1.500   0.3957   0.05744   0.05117  -0.1191   0.8484   0.0957
  -1.250   0.4237   0.05304   0.04681  -0.1216   0.8419   0.1020
  -1.000   0.4564   0.05300   0.04663  -0.1249   0.8317   0.1096
  -0.750   0.4987   0.05238   0.04580  -0.1291   0.8239   0.1213
  -0.500   0.5207   0.05015   0.04356  -0.1304   0.8157   0.1305
  -0.250   0.5496   0.04926   0.04258  -0.1325   0.8076   0.1393
   0.000   0.5864   0.04819   0.04138  -0.1355   0.8002   0.1532
   0.250   0.6091   0.04797   0.04107  -0.1367   0.7917   0.1662
   0.500   0.6487   0.04683   0.03976  -0.1396   0.7851   0.1888
   0.750   0.6676   0.04750   0.04032  -0.1402   0.7764   0.2111
   1.000   0.7030   0.04546   0.03821  -0.1425   0.7705   0.2562
   1.500   0.7458   0.04319   0.03584  -0.1440   0.7565   0.4136
   1.750   0.7584   0.04360   0.03621  -0.1440   0.7486   0.4535
   2.000   0.8018   0.04277   0.03509  -0.1465   0.7422   0.5020
   2.250   0.8163   0.04415   0.03633  -0.1468   0.7343   0.5131
   2.500   0.8588   0.04439   0.03629  -0.1490   0.7280   0.5147
   2.750   0.8697   0.04641   0.03821  -0.1489   0.7200   0.5049
   3.000   0.9081   0.04774   0.03926  -0.1499   0.7136   0.4450
   3.250   0.9098   0.05053   0.04200  -0.1488   0.7060   0.4089
   3.500   0.9455   0.05186   0.04311  -0.1491   0.6995   0.3413
   3.750   0.9409   0.05471   0.04591  -0.1473   0.6927   0.3231
   4.000   0.9695   0.05625   0.04729  -0.1471   0.6861   0.2659
   4.250   0.9722   0.05875   0.04971  -0.1458   0.6797   0.2451
   4.500   0.9918   0.06033   0.05112  -0.1454   0.6729   0.2275
   4.750   1.0054   0.06208   0.05274  -0.1449   0.6661   0.2402
   5.000   1.0189   0.06392   0.05445  -0.1443   0.6594   0.2387
   5.250   1.0350   0.06537   0.05584  -0.1440   0.6518   0.2675
   5.500   1.0493   0.06722   0.05760  -0.1435   0.6445   0.2756
   5.750   1.0571   0.06944   0.05981  -0.1427   0.6365   0.2885
   6.000   1.0932   0.06995   0.06032  -0.1430   0.6264   0.3346
   6.250   1.0776   0.07386   0.06429  -0.1418   0.6203   0.3365
   6.500   1.0979   0.07497   0.06597  -0.1413   0.6103   1.0000
   6.750   1.1307   0.07611   0.06702  -0.1405   0.5986   1.0000
   7.000   1.1068   0.08073   0.07172  -0.1395   0.5924   1.0000
   7.250   1.1234   0.08283   0.07371  -0.1386   0.5806   1.0000
   7.500   1.1424   0.08475   0.07555  -0.1376   0.5681   1.0000
   7.750   1.1597   0.08666   0.07740  -0.1365   0.5547   1.0000
   8.000   1.1772   0.08852   0.07927  -0.1354   0.5411   1.0000
   8.250   1.1902   0.09058   0.08137  -0.1343   0.5270   1.0000
   8.500   1.2015   0.09278   0.08363  -0.1331   0.5128   1.0000
   8.750   1.2086   0.09526   0.08619  -0.1320   0.4981   1.0000
   9.000   1.2173   0.09772   0.08886  -0.1309   0.4837   1.0000
   9.250   1.2218   0.10043   0.09166  -0.1298   0.4686   1.0000
   9.500   1.2280   0.10313   0.09446  -0.1289   0.4539   1.0000
   9.750   1.2334   0.10583   0.09727  -0.1279   0.4384   1.0000
  10.000   1.2400   0.10852   0.10009  -0.1270   0.4234   1.0000
  10.250   1.2499   0.11065   0.10235  -0.1258   0.4070   1.0000
  10.500   1.2660   0.11198   0.10385  -0.1241   0.3906   1.0000
  10.750   1.2995   0.11031   0.10244  -0.1206   0.3716   1.0000
  11.000   1.2980   0.11397   0.10621  -0.1202   0.3568   1.0000
  11.250   1.2968   0.11762   0.11012  -0.1199   0.3415   1.0000
  11.500   1.2981   0.12104   0.11368  -0.1194   0.3267   1.0000
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