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=100,000 Ncrit=5


Details Polar file
Airfoil: E387 (e387-il)
Reynolds number: 100,000
Max Cl/Cd: 60.95 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-e387-il-100000-n5.txt
Download as CSV file: xf-e387-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3381   0.09095   0.08633  -0.0331   1.0000   0.0499
  -7.750  -0.3356   0.08800   0.08344  -0.0338   1.0000   0.0504
  -7.500  -0.3359   0.08516   0.08069  -0.0343   1.0000   0.0508
  -7.250  -0.3394   0.08244   0.07808  -0.0347   1.0000   0.0509
  -7.000  -0.3418   0.07955   0.07530  -0.0359   1.0000   0.0508
  -6.500  -0.3175   0.06403   0.05970  -0.0545   0.9790   0.0269
  -6.250  -0.2922   0.05927   0.05486  -0.0602   0.9645   0.0259
  -6.000  -0.2644   0.05334   0.04877  -0.0676   0.9490   0.0248
  -5.750  -0.2355   0.04672   0.04185  -0.0746   0.9337   0.0237
  -5.500  -0.2070   0.03972   0.03434  -0.0803   0.9189   0.0225
  -5.250  -0.1789   0.03314   0.02689  -0.0838   0.9048   0.0215
  -5.000  -0.1513   0.03018   0.02350  -0.0853   0.8918   0.0219
  -4.750  -0.1237   0.02823   0.02119  -0.0862   0.8790   0.0235
  -4.500  -0.0957   0.02583   0.01825  -0.0866   0.8671   0.0249
  -4.250  -0.0678   0.02362   0.01551  -0.0866   0.8559   0.0254
  -4.000  -0.0407   0.02183   0.01330  -0.0862   0.8439   0.0259
  -3.750  -0.0136   0.02039   0.01152  -0.0858   0.8327   0.0266
  -3.500   0.0131   0.01913   0.01003  -0.0853   0.8226   0.0278
  -3.250   0.0396   0.01820   0.00899  -0.0850   0.8126   0.0300
  -3.000   0.0663   0.01757   0.00820  -0.0846   0.8022   0.0350
  -2.750   0.0929   0.01679   0.00733  -0.0843   0.7932   0.0417
  -2.500   0.1198   0.01603   0.00646  -0.0838   0.7841   0.0579
  -2.250   0.1458   0.01526   0.00603  -0.0837   0.7751   0.1292
  -2.000   0.1715   0.01454   0.00575  -0.0835   0.7675   0.2503
  -1.750   0.1967   0.01397   0.00558  -0.0832   0.7585   0.3842
  -1.500   0.2201   0.01333   0.00544  -0.0821   0.7513   0.5649
  -1.250   0.2394   0.01269   0.00542  -0.0792   0.7432   0.7821
  -1.000   0.2876   0.01237   0.00503  -0.0826   0.7366   1.0000
  -0.750   0.3140   0.01248   0.00491  -0.0823   0.7283   1.0000
  -0.500   0.3409   0.01261   0.00479  -0.0820   0.7217   1.0000
  -0.250   0.3675   0.01274   0.00475  -0.0818   0.7139   1.0000
   0.000   0.3944   0.01288   0.00468  -0.0816   0.7077   1.0000
   0.250   0.4210   0.01303   0.00471  -0.0814   0.7001   1.0000
   0.500   0.4481   0.01318   0.00469  -0.0812   0.6943   1.0000
   0.750   0.4746   0.01335   0.00479  -0.0810   0.6867   1.0000
   1.000   0.5016   0.01351   0.00482  -0.0808   0.6808   1.0000
   1.250   0.5283   0.01370   0.00495  -0.0806   0.6739   1.0000
   1.500   0.5551   0.01388   0.00505  -0.0804   0.6676   1.0000
   1.750   0.5819   0.01407   0.00519  -0.0802   0.6615   1.0000
   2.000   0.6085   0.01427   0.00536  -0.0800   0.6547   1.0000
   2.250   0.6356   0.01446   0.00549  -0.0798   0.6493   1.0000
   2.500   0.6618   0.01469   0.00575  -0.0796   0.6420   1.0000
   2.750   0.6888   0.01488   0.00592  -0.0794   0.6364   1.0000
   3.000   0.7150   0.01513   0.00621  -0.0792   0.6292   1.0000
   3.250   0.7417   0.01533   0.00641  -0.0789   0.6230   1.0000
   3.500   0.7678   0.01557   0.00671  -0.0787   0.6157   1.0000
   3.750   0.7943   0.01577   0.00696  -0.0784   0.6086   1.0000
   4.000   0.8202   0.01600   0.00726  -0.0781   0.6004   1.0000
   4.250   0.8467   0.01617   0.00745  -0.0777   0.5927   1.0000
   4.500   0.8720   0.01639   0.00782  -0.0773   0.5828   1.0000
   4.750   0.8977   0.01656   0.00806  -0.0768   0.5733   1.0000
   5.000   0.9237   0.01670   0.00825  -0.0763   0.5634   1.0000
   5.250   0.9485   0.01688   0.00857  -0.0757   0.5514   1.0000
   5.500   0.9734   0.01705   0.00888  -0.0751   0.5387   1.0000
   5.750   0.9980   0.01720   0.00915  -0.0744   0.5248   1.0000
   6.000   1.0224   0.01735   0.00942  -0.0736   0.5094   1.0000
   6.250   1.0465   0.01750   0.00967  -0.0728   0.4922   1.0000
   6.500   1.0697   0.01771   0.01006  -0.0719   0.4716   1.0000
   6.750   1.0923   0.01793   0.01037  -0.0709   0.4476   1.0000
   7.000   1.1123   0.01825   0.01068  -0.0695   0.4075   1.0000
   7.250   1.1282   0.01890   0.01107  -0.0676   0.3417   1.0000
   7.500   1.1368   0.02029   0.01188  -0.0651   0.2553   1.0000
   7.750   1.1439   0.02201   0.01314  -0.0628   0.1838   1.0000
   8.000   1.1510   0.02374   0.01446  -0.0607   0.1246   1.0000
   8.250   1.1597   0.02530   0.01579  -0.0586   0.0840   1.0000
   8.500   1.1670   0.02693   0.01725  -0.0564   0.0551   1.0000
   8.750   1.1731   0.02859   0.01886  -0.0540   0.0398   1.0000
   9.000   1.1756   0.03029   0.02053  -0.0511   0.0335   1.0000
   9.250   1.1808   0.03184   0.02224  -0.0487   0.0300   1.0000
   9.500   1.1850   0.03352   0.02404  -0.0466   0.0273   1.0000
   9.750   1.1865   0.03552   0.02614  -0.0446   0.0255   1.0000
  10.000   1.1910   0.03738   0.02816  -0.0430   0.0238   1.0000
  10.250   1.1952   0.03936   0.03031  -0.0416   0.0226   1.0000
  10.500   1.1990   0.04150   0.03259  -0.0404   0.0218   1.0000
  10.750   1.2029   0.04372   0.03495  -0.0392   0.0211   1.0000
  11.000   1.2072   0.04601   0.03735  -0.0382   0.0205   1.0000
  11.250   1.2117   0.04839   0.03983  -0.0373   0.0199   1.0000
  11.500   1.2172   0.05083   0.04237  -0.0363   0.0195   1.0000
  11.750   1.2247   0.05334   0.04498  -0.0352   0.0190   1.0000
  12.000   1.2338   0.05579   0.04767  -0.0343   0.0188   1.0000
  12.250   1.2416   0.05852   0.05064  -0.0334   0.0185   1.0000
  12.500   1.2466   0.06155   0.05394  -0.0328   0.0182   1.0000
  12.750   1.2478   0.06497   0.05765  -0.0325   0.0179   1.0000
  13.000   1.2457   0.06872   0.06167  -0.0325   0.0176   1.0000
  13.250   1.2402   0.07281   0.06605  -0.0329   0.0172   1.0000
  13.500   1.2327   0.07728   0.07078  -0.0337   0.0170   1.0000
  13.750   1.2229   0.08215   0.07590  -0.0350   0.0167   1.0000
  14.000   1.2109   0.08749   0.08150  -0.0368   0.0166   1.0000
  14.250   1.1972   0.09332   0.08757  -0.0392   0.0165   1.0000
  14.500   1.1812   0.09989   0.09438  -0.0422   0.0165   1.0000
  14.750   1.1634   0.10725   0.10198  -0.0461   0.0166   1.0000
  15.000   1.1441   0.11552   0.11048  -0.0509   0.0167   1.0000
  15.250   1.1228   0.12498   0.12014  -0.0568   0.0170   1.0000
  15.500   1.1005   0.13566   0.13100  -0.0638   0.0174   1.0000
<< Back to E387 (e387-il)

Polar data table (+)

Polar graphs


<< Back to E387 (e387-il)