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E71 (5.15%) (e71-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: E71 (5.15%) (e71-il)
Reynolds number: 1,000,000
Max Cl/Cd: 139.05 at α=1.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e71-il-1000000-n5.txt
Download as CSV file: xf-e71-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E71  (5.15%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3139   0.10048   0.09878  -0.0416   0.9917   0.0041
  -8.500  -0.3025   0.09767   0.09598  -0.0437   0.9904   0.0049
  -8.250  -0.2993   0.09030   0.08862  -0.0481   0.9883   0.0033
  -8.000  -0.2883   0.08630   0.08463  -0.0514   0.9866   0.0033
  -7.750  -0.2756   0.08258   0.08091  -0.0551   0.9851   0.0033
  -7.500  -0.2591   0.08017   0.07851  -0.0583   0.9839   0.0035
  -7.250  -0.2426   0.07626   0.07461  -0.0632   0.9826   0.0036
  -7.000  -0.2360   0.07330   0.07166  -0.0646   0.9774   0.0036
  -6.750  -0.2173   0.07014   0.06850  -0.0691   0.9746   0.0039
  -6.500  -0.1937   0.06589   0.06424  -0.0759   0.9726   0.0042
  -6.250  -0.1649   0.06115   0.05949  -0.0843   0.9711   0.0048
  -5.000   0.0505   0.02297   0.02050  -0.1458   0.9589   0.0078
  -4.750   0.0854   0.02146   0.01885  -0.1490   0.9583   0.0084
  -4.500   0.1243   0.01869   0.01581  -0.1531   0.9577   0.0092
  -4.250   0.1565   0.01618   0.01299  -0.1551   0.9548   0.0097
  -4.000   0.1881   0.01409   0.01060  -0.1566   0.9514   0.0099
  -3.750   0.2216   0.01272   0.00899  -0.1582   0.9494   0.0106
  -3.500   0.2574   0.01096   0.00693  -0.1602   0.9481   0.0100
  -3.250   0.2925   0.00968   0.00542  -0.1619   0.9467   0.0096
  -3.000   0.3279   0.00866   0.00424  -0.1636   0.9454   0.0093
  -2.750   0.3584   0.00794   0.00340  -0.1642   0.9414   0.0091
  -2.500   0.3905   0.00735   0.00272  -0.1651   0.9366   0.0089
  -2.250   0.4273   0.00683   0.00210  -0.1671   0.9327   0.0089
  -2.000   0.4614   0.00645   0.00164  -0.1684   0.9256   0.0090
  -1.750   0.4984   0.00612   0.00123  -0.1703   0.9185   0.0096
  -1.500   0.5320   0.00593   0.00097  -0.1715   0.9072   0.0117
  -1.000   0.5934   0.00583   0.00073  -0.1726   0.8741   0.0133
  -0.750   0.6214   0.00584   0.00064  -0.1726   0.8549   0.0139
  -0.500   0.6485   0.00589   0.00057  -0.1723   0.8337   0.0157
  -0.250   0.6745   0.00598   0.00054  -0.1717   0.8082   0.0175
   0.000   0.7003   0.00605   0.00057  -0.1712   0.7804   0.0451
   0.250   0.7273   0.00592   0.00065  -0.1712   0.7525   0.1804
   0.500   0.7535   0.00590   0.00076  -0.1710   0.7219   0.2882
   0.750   0.7790   0.00595   0.00090  -0.1707   0.6841   0.3920
   1.000   0.8053   0.00587   0.00115  -0.1707   0.6362   0.6253
   1.250   0.8301   0.00597   0.00136  -0.1702   0.5868   0.7638
   1.500   0.8520   0.00614   0.00155  -0.1689   0.5357   0.8653
   1.750   0.8693   0.00631   0.00165  -0.1665   0.4859   1.0000
   2.000   0.8932   0.00678   0.00187  -0.1658   0.4248   1.0000
   2.250   0.9162   0.00738   0.00212  -0.1650   0.3484   1.0000
   2.500   0.9357   0.00848   0.00253  -0.1637   0.2095   1.0000
   2.750   0.9580   0.00925   0.00288  -0.1628   0.1247   1.0000
   3.000   0.9818   0.00983   0.00319  -0.1622   0.0718   1.0000
   3.250   1.0056   0.01044   0.00354  -0.1615   0.0251   1.0000
   3.500   1.0306   0.01087   0.00385  -0.1609   0.0068   1.0000
   3.750   1.0567   0.01111   0.00413  -0.1605   0.0051   1.0000
   4.000   1.0826   0.01139   0.00446  -0.1601   0.0041   1.0000
   4.250   1.1081   0.01174   0.00489  -0.1596   0.0033   1.0000
   4.500   1.1335   0.01210   0.00529  -0.1590   0.0032   1.0000
   4.750   1.1583   0.01253   0.00579  -0.1584   0.0031   1.0000
   5.000   1.1827   0.01305   0.00639  -0.1577   0.0030   1.0000
   5.250   1.2069   0.01359   0.00699  -0.1569   0.0028   1.0000
   5.500   1.2308   0.01416   0.00768  -0.1561   0.0026   1.0000
   5.750   1.2546   0.01470   0.00828  -0.1553   0.0024   1.0000
   6.000   1.2778   0.01538   0.00903  -0.1544   0.0022   1.0000
   6.250   1.3004   0.01612   0.00986  -0.1534   0.0021   1.0000
   6.500   1.3227   0.01691   0.01073  -0.1524   0.0019   1.0000
   6.750   1.3450   0.01768   0.01158  -0.1514   0.0018   1.0000
   7.000   1.3670   0.01850   0.01248  -0.1504   0.0017   1.0000
   7.250   1.3885   0.01938   0.01344  -0.1493   0.0016   1.0000
   7.500   1.4078   0.02072   0.01490  -0.1479   0.0014   1.0000
   7.750   1.4223   0.02343   0.01792  -0.1455   0.0012   1.0000
   8.000   1.4427   0.02459   0.01924  -0.1442   0.0012   1.0000
   8.250   1.4621   0.02598   0.02080  -0.1428   0.0011   1.0000
   8.500   1.4794   0.02782   0.02286  -0.1410   0.0011   1.0000
   8.750   1.4941   0.03018   0.02550  -0.1388   0.0010   1.0000
   9.000   1.5058   0.03293   0.02857  -0.1363   0.0010   1.0000
   9.250   1.5131   0.03630   0.03230  -0.1332   0.0010   1.0000
   9.500   1.5158   0.03996   0.03632  -0.1296   0.0010   1.0000
   9.750   1.5129   0.04394   0.04065  -0.1255   0.0010   1.0000
  10.000   1.5015   0.04799   0.04503  -0.1204   0.0010   1.0000
  10.250   1.4835   0.05156   0.04884  -0.1146   0.0010   1.0000
  10.500   1.4661   0.05531   0.05283  -0.1100   0.0010   1.0000
  10.750   1.4456   0.05982   0.05756  -0.1064   0.0010   1.0000
  11.000   1.4247   0.06477   0.06272  -0.1041   0.0010   1.0000
  11.250   1.4042   0.07024   0.06836  -0.1034   0.0010   1.0000
  11.500   1.3816   0.07682   0.07512  -0.1045   0.0010   1.0000
  11.750   1.3577   0.08481   0.08329  -0.1078   0.0010   1.0000
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