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

E387 (e387-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 50,000
Max Cl/Cd: 38.66 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e387-il-50000-n5.txt
Download as CSV file: xf-e387-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: E387                                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3401   0.09787   0.09138  -0.0300   1.0000   0.1108
  -7.750  -0.3536   0.09657   0.09027  -0.0328   1.0000   0.1142
  -7.500  -0.3631   0.09452   0.08838  -0.0370   1.0000   0.1149
  -7.250  -0.3546   0.09031   0.08426  -0.0355   1.0000   0.1160
  -7.000  -0.3471   0.08216   0.07605  -0.0407   1.0000   0.0590
  -6.750  -0.3434   0.07928   0.07326  -0.0390   1.0000   0.0565
  -6.500  -0.3448   0.07623   0.07032  -0.0395   1.0000   0.0543
  -6.000  -0.3558   0.06783   0.06187  -0.0458   1.0000   0.0469
  -5.750  -0.3445   0.06446   0.05850  -0.0469   0.9948   0.0461
  -5.500  -0.3144   0.05923   0.05311  -0.0533   0.9827   0.0448
  -5.250  -0.2819   0.05371   0.04732  -0.0601   0.9711   0.0435
  -5.000  -0.2480   0.04825   0.04146  -0.0664   0.9596   0.0425
  -4.750  -0.2141   0.04330   0.03597  -0.0714   0.9484   0.0418
  -4.500  -0.1782   0.03889   0.03095  -0.0756   0.9387   0.0416
  -4.250  -0.1398   0.03517   0.02656  -0.0791   0.9304   0.0427
  -4.000  -0.1052   0.03232   0.02302  -0.0811   0.9203   0.0455
  -3.750  -0.0682   0.02981   0.01991  -0.0830   0.9122   0.0480
  -3.500  -0.0352   0.02790   0.01771  -0.0842   0.9028   0.0509
  -3.250  -0.0025   0.02630   0.01579  -0.0848   0.8934   0.0550
  -3.000   0.0326   0.02492   0.01417  -0.0858   0.8857   0.0645
  -2.750   0.0623   0.02386   0.01295  -0.0860   0.8754   0.0805
  -2.500   0.0945   0.02274   0.01184  -0.0869   0.8669   0.1281
  -2.250   0.1247   0.02143   0.01100  -0.0876   0.8581   0.2265
  -2.000   0.1498   0.02026   0.01062  -0.0874   0.8486   0.4094
  -1.750   0.1687   0.01902   0.01048  -0.0841   0.8413   0.7034
  -1.500   0.2178   0.01853   0.00985  -0.0872   0.8329   1.0000
  -1.250   0.2476   0.01867   0.00953  -0.0875   0.8246   1.0000
  -1.000   0.2740   0.01889   0.00940  -0.0873   0.8149   1.0000
  -0.750   0.3006   0.01912   0.00930  -0.0872   0.8060   1.0000
  -0.500   0.3288   0.01931   0.00919  -0.0872   0.7981   1.0000
  -0.250   0.3537   0.01961   0.00927  -0.0868   0.7888   1.0000
   0.000   0.3831   0.01979   0.00921  -0.0869   0.7821   1.0000
   0.250   0.4072   0.02016   0.00940  -0.0866   0.7726   1.0000
   0.500   0.4351   0.02040   0.00947  -0.0865   0.7657   1.0000
   0.750   0.4600   0.02077   0.00971  -0.0862   0.7569   1.0000
   1.000   0.4868   0.02107   0.00989  -0.0860   0.7498   1.0000
   1.250   0.5121   0.02144   0.01017  -0.0857   0.7417   1.0000
   1.500   0.5381   0.02179   0.01044  -0.0855   0.7344   1.0000
   1.750   0.5636   0.02218   0.01077  -0.0852   0.7268   1.0000
   2.000   0.5890   0.02257   0.01114  -0.0849   0.7194   1.0000
   2.250   0.6145   0.02297   0.01151  -0.0846   0.7119   1.0000
   2.500   0.6393   0.02342   0.01195  -0.0842   0.7044   1.0000
   2.750   0.6648   0.02383   0.01238  -0.0839   0.6970   1.0000
   3.000   0.6889   0.02433   0.01293  -0.0835   0.6893   1.0000
   3.250   0.7145   0.02473   0.01337  -0.0831   0.6820   1.0000
   3.500   0.7377   0.02530   0.01400  -0.0826   0.6738   1.0000
   3.750   0.7640   0.02565   0.01441  -0.0822   0.6667   1.0000
   4.000   0.7859   0.02629   0.01519  -0.0816   0.6575   1.0000
   4.250   0.8139   0.02651   0.01548  -0.0812   0.6508   1.0000
   4.500   0.8344   0.02719   0.01631  -0.0804   0.6403   1.0000
   4.750   0.8589   0.02761   0.01689  -0.0798   0.6315   1.0000
   5.000   0.8847   0.02787   0.01729  -0.0791   0.6225   1.0000
   5.250   0.9059   0.02843   0.01801  -0.0781   0.6111   1.0000
   5.500   0.9292   0.02879   0.01855  -0.0772   0.6000   1.0000
   5.750   0.9549   0.02891   0.01887  -0.0762   0.5890   1.0000
   6.000   0.9817   0.02886   0.01900  -0.0752   0.5774   1.0000
   6.250   1.0046   0.02902   0.01937  -0.0739   0.5634   1.0000
   6.500   1.0277   0.02907   0.01962  -0.0725   0.5481   1.0000
   6.750   1.0469   0.02932   0.02017  -0.0709   0.5301   1.0000
   7.000   1.0681   0.02930   0.02039  -0.0691   0.5108   1.0000
   7.250   1.0905   0.02906   0.02036  -0.0673   0.4897   1.0000
   7.500   1.1089   0.02907   0.02060  -0.0652   0.4642   1.0000
   7.750   1.1256   0.02915   0.02086  -0.0629   0.4337   1.0000
   8.000   1.1388   0.02946   0.02135  -0.0603   0.3947   1.0000
   8.250   1.1488   0.03001   0.02183  -0.0574   0.3439   1.0000
   8.500   1.1526   0.03118   0.02265  -0.0542   0.2846   1.0000
   8.750   1.1482   0.03318   0.02422  -0.0509   0.2301   1.0000
   9.000   1.1384   0.03567   0.02632  -0.0478   0.1850   1.0000
   9.250   1.1292   0.03854   0.02887  -0.0456   0.1459   1.0000
   9.500   1.1210   0.04168   0.03170  -0.0441   0.1150   1.0000
   9.750   1.1165   0.04476   0.03467  -0.0430   0.0928   1.0000
  10.000   1.1109   0.04813   0.03791  -0.0420   0.0775   1.0000
  10.250   1.1088   0.05128   0.04106  -0.0411   0.0665   1.0000
  10.500   1.1092   0.05427   0.04411  -0.0402   0.0584   1.0000
  10.750   1.1095   0.05729   0.04715  -0.0396   0.0530   1.0000
  11.000   1.1149   0.05988   0.04995  -0.0387   0.0478   1.0000
  11.250   1.1194   0.06259   0.05271  -0.0379   0.0446   1.0000
  11.500   1.1311   0.06479   0.05506  -0.0364   0.0422   1.0000
  11.750   1.1489   0.06680   0.05742  -0.0345   0.0398   1.0000
  12.000   1.1636   0.06933   0.06026  -0.0332   0.0381   1.0000
  12.250   1.1712   0.07249   0.06367  -0.0326   0.0367   1.0000
  12.500   1.1742   0.07599   0.06740  -0.0325   0.0355   1.0000
  12.750   1.1751   0.07973   0.07128  -0.0326   0.0344   1.0000
  13.000   1.1731   0.08408   0.07584  -0.0330   0.0336   1.0000
  13.250   1.1624   0.08934   0.08144  -0.0345   0.0333   1.0000
  13.500   1.1500   0.09502   0.08741  -0.0365   0.0331   1.0000
  13.750   1.1355   0.10126   0.09391  -0.0392   0.0331   1.0000
  14.000   1.1196   0.10802   0.10091  -0.0425   0.0331   1.0000
  14.250   1.1037   0.11523   0.10827  -0.0464   0.0332   1.0000
  14.500   1.0875   0.12306   0.11627  -0.0510   0.0334   1.0000
  14.750   1.0717   0.13143   0.12477  -0.0560   0.0336   1.0000
<< Back to E387 (e387-il)

Polar data table (+)

Polar graphs


<< Back to E387 (e387-il)