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Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: Eiffel 10 (Wright) - 1903 Wright Flyer airfoil (eiffel10-il)
Reynolds number: 50,000
Max Cl/Cd: 25.46 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-eiffel10-il-50000.txt
Download as CSV file: xf-eiffel10-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Eiffel 10 (Wright) - 1903 Wright Flyer 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4182   0.11835   0.11074  -0.0036   1.0000   0.0826
  -8.500  -0.4143   0.11765   0.11012  -0.0062   1.0000   0.0838
  -8.250  -0.4082   0.11779   0.11033  -0.0112   1.0000   0.0844
  -8.000  -0.3971   0.11224   0.10486  -0.0104   1.0000   0.0855
  -7.750  -0.3854   0.10706   0.09971  -0.0089   1.0000   0.0878
  -7.500  -0.3746   0.10393   0.09664  -0.0099   1.0000   0.0904
  -7.250  -0.3634   0.10135   0.09412  -0.0119   1.0000   0.0932
  -7.000  -0.3499   0.09976   0.09259  -0.0163   1.0000   0.0962
  -6.750  -0.3266   0.10078   0.09362  -0.0274   1.0000   0.0978
  -6.500  -0.3220   0.09409   0.08707  -0.0221   1.0000   0.0994
  -6.250  -0.3113   0.09017   0.08322  -0.0212   1.0000   0.1025
  -6.000  -0.2966   0.08743   0.08055  -0.0231   1.0000   0.1066
  -5.750  -0.2690   0.08698   0.08010  -0.0322   1.0000   0.1114
  -5.500  -0.2555   0.08323   0.07646  -0.0333   1.0000   0.1133
  -5.250  -0.2481   0.07929   0.07264  -0.0308   1.0000   0.1167
  -5.000  -0.2320   0.07678   0.07020  -0.0326   1.0000   0.1222
  -4.750  -0.1985   0.07575   0.06916  -0.0416   1.0000   0.1278
  -4.500  -0.1963   0.07169   0.06526  -0.0376   1.0000   0.1310
  -4.250  -0.1809   0.06929   0.06295  -0.0386   1.0000   0.1377
  -4.000  -0.1534   0.06735   0.06102  -0.0440   1.0000   0.1444
  -3.750  -0.1462   0.06441   0.05821  -0.0419   1.0000   0.1499
  -3.500  -0.1155   0.06270   0.05650  -0.0476   1.0000   0.1601
  -3.250  -0.1073   0.05987   0.05380  -0.0456   1.0000   0.1671
  -3.000  -0.0825   0.05770   0.05168  -0.0488   1.0000   0.1782
  -2.750  -0.0570   0.05573   0.04975  -0.0519   1.0000   0.1925
  -2.500  -0.0358   0.05352   0.04762  -0.0534   1.0000   0.2086
  -2.250  -0.0179   0.05114   0.04536  -0.0538   1.0000   0.2265
  -2.000   0.0078   0.04935   0.04364  -0.0562   1.0000   0.2564
  -1.750   0.0264   0.04710   0.04154  -0.0565   1.0000   0.2897
  -1.500   0.0404   0.04457   0.03923  -0.0552   1.0000   0.3276
  -0.750   0.1902   0.02939   0.02516  -0.0600   0.9219   0.6661
  -0.500   0.2488   0.02578   0.02160  -0.0623   0.8472   0.7108
  -0.250   0.3014   0.02408   0.01951  -0.0660   0.7352   0.7093
   0.000   0.3595   0.02730   0.01928  -0.0749   0.1423   0.6410
   0.250   0.4761   0.03136   0.02169  -0.0959   0.1214   0.3360
   0.500   0.5239   0.03132   0.02109  -0.0983   0.1158   0.2322
   0.750   0.5609   0.03128   0.02063  -0.0987   0.1115   0.1869
   1.000   0.5932   0.03108   0.02022  -0.0985   0.1089   0.1673
   1.250   0.6244   0.03103   0.01995  -0.0980   0.1075   0.1544
   1.500   0.6550   0.03112   0.01978  -0.0971   0.1072   0.1442
   1.750   0.6836   0.03130   0.01971  -0.0958   0.1074   0.1385
   2.000   0.7126   0.03156   0.01971  -0.0943   0.1081   0.1337
   2.250   0.7424   0.03204   0.01990  -0.0927   0.1090   0.1310
   2.500   0.7729   0.03284   0.02044  -0.0913   0.1101   0.1314
   2.750   0.8033   0.03296   0.02064  -0.0899   0.1127   0.1359
   3.000   0.8347   0.03362   0.02146  -0.0888   0.1164   0.1475
   3.250   0.8665   0.03480   0.02279  -0.0879   0.1206   0.1722
   3.500   0.8946   0.03522   0.02444  -0.0868   0.1241   1.0000
   3.750   0.9256   0.03635   0.02548  -0.0852   0.1299   1.0000
   4.000   0.9560   0.03857   0.02774  -0.0841   0.1380   1.0000
   4.250   0.9866   0.04036   0.02988  -0.0829   0.1485   1.0000
   4.500   1.0153   0.04420   0.03356  -0.0824   0.1573   1.0000
   4.750   1.0449   0.04656   0.03652  -0.0813   0.1729   1.0000
   5.000   1.0749   0.04885   0.03993  -0.0806   0.1988   1.0000
   5.250   1.1033   0.05342   0.04540  -0.0813   0.2335   1.0000
   5.500   1.1268   0.06273   0.05603  -0.0879   0.3055   1.0000
   6.250   0.9296   0.10786   0.10315  -0.1424   0.5759   1.0000
   6.500   0.9239   0.11119   0.10631  -0.1412   0.5645   1.0000
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