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N-13 (n13-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: N-13 (n13-il)
Reynolds number: 50,000
Max Cl/Cd: 28.97 at α=4.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-n13-il-50000.txt
Download as CSV file: xf-n13-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: N-13                                            
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.7324   0.08406   0.07670  -0.0379   1.0000   0.1412
 -10.500  -0.7455   0.07879   0.07142  -0.0381   1.0000   0.1399
 -10.250  -0.7687   0.07393   0.06654  -0.0371   1.0000   0.1383
 -10.000  -0.7963   0.06978   0.06235  -0.0343   1.0000   0.1366
  -9.750  -0.8227   0.06548   0.05790  -0.0312   1.0000   0.1350
  -9.500  -0.8452   0.06134   0.05355  -0.0276   1.0000   0.1341
  -9.250  -0.8598   0.05754   0.04944  -0.0239   1.0000   0.1346
  -9.000  -0.8701   0.05404   0.04561  -0.0200   1.0000   0.1369
  -8.750  -0.8794   0.05069   0.04180  -0.0158   1.0000   0.1395
  -8.500  -0.8767   0.04752   0.03840  -0.0127   1.0000   0.1446
  -8.250  -0.8695   0.04506   0.03573  -0.0098   1.0000   0.1523
  -8.000  -0.8629   0.04240   0.03281  -0.0067   1.0000   0.1599
  -7.750  -0.8564   0.04028   0.03030  -0.0034   1.0000   0.1695
  -7.500  -0.8404   0.03812   0.02813  -0.0015   1.0000   0.1809
  -7.250  -0.8263   0.03606   0.02593   0.0008   1.0000   0.1928
  -7.000  -0.8104   0.03390   0.02353   0.0030   1.0000   0.2050
  -6.750  -0.7930   0.03205   0.02162   0.0049   1.0000   0.2217
  -6.500  -0.7741   0.03014   0.01966   0.0067   1.0000   0.2425
  -6.250  -0.7540   0.02837   0.01804   0.0084   1.0000   0.2696
  -6.000  -0.7378   0.02702   0.01685   0.0107   1.0000   0.3026
  -5.750  -0.7215   0.02587   0.01578   0.0131   1.0000   0.3365
  -5.500  -0.7051   0.02485   0.01505   0.0156   1.0000   0.3747
  -5.250  -0.6921   0.02392   0.01443   0.0187   1.0000   0.4248
  -5.000  -0.6801   0.02307   0.01404   0.0225   1.0000   0.4908
  -4.750  -0.6686   0.02272   0.01415   0.0273   1.0000   0.5675
  -4.500  -0.6530   0.02290   0.01461   0.0322   1.0000   0.6399
  -4.250  -0.6312   0.02320   0.01497   0.0360   1.0000   0.6979
  -4.000  -0.6001   0.02374   0.01543   0.0381   1.0000   0.7444
  -3.750  -0.5573   0.02463   0.01613   0.0382   1.0000   0.7837
  -3.500  -0.5040   0.02580   0.01704   0.0363   1.0000   0.8189
  -3.250  -0.3777   0.02850   0.01918   0.0235   1.0000   0.8579
  -3.000  -0.2954   0.02929   0.01962   0.0152   1.0000   0.8934
  -2.750  -0.2109   0.02932   0.01934   0.0052   1.0000   0.9259
  -2.500  -0.1392   0.02867   0.01847  -0.0038   1.0000   0.9540
  -2.250  -0.0740   0.02755   0.01718  -0.0126   1.0000   0.9757
  -2.000  -0.0090   0.02629   0.01578  -0.0219   1.0000   0.9967
  -1.750   0.0073   0.02560   0.01507  -0.0221   1.0000   1.0000
  -1.500   0.0120   0.02510   0.01459  -0.0199   1.0000   1.0000
  -1.250   0.0153   0.02467   0.01418  -0.0174   1.0000   1.0000
  -1.000   0.0170   0.02431   0.01385  -0.0146   1.0000   1.0000
  -0.750   0.0169   0.02401   0.01357  -0.0115   1.0000   1.0000
  -0.500   0.0150   0.02377   0.01335  -0.0080   1.0000   1.0000
  -0.250   0.0115   0.02357   0.01317  -0.0043   1.0000   1.0000
   0.000   0.0066   0.02343   0.01305  -0.0003   1.0000   1.0000
   0.250   0.0009   0.02336   0.01298   0.0038   1.0000   1.0000
   0.500  -0.0043   0.02336   0.01298   0.0078   1.0000   1.0000
   0.750  -0.0076   0.02345   0.01305   0.0116   1.0000   1.0000
   1.000  -0.0086   0.02362   0.01320   0.0150   1.0000   1.0000
   1.250  -0.0072   0.02387   0.01342   0.0180   1.0000   1.0000
   1.500  -0.0038   0.02418   0.01372   0.0207   1.0000   1.0000
   1.750   0.0011   0.02456   0.01410   0.0231   1.0000   1.0000
   2.000   0.0070   0.02501   0.01454   0.0252   1.0000   1.0000
   2.250   0.0136   0.02554   0.01508   0.0271   1.0000   1.0000
   2.500   0.0559   0.02659   0.01625   0.0220   0.9880   1.0000
   2.750   0.1420   0.02783   0.01777   0.0092   0.9579   1.0000
   3.000   0.2259   0.02841   0.01866  -0.0020   0.9236   1.0000
   3.250   0.3284   0.02826   0.01894  -0.0149   0.8868   1.0000
   3.500   0.4416   0.02686   0.01811  -0.0277   0.8448   1.0000
   3.750   0.5247   0.02488   0.01658  -0.0336   0.7949   1.0000
   4.000   0.5889   0.02268   0.01458  -0.0350   0.7307   1.0000
   4.250   0.6245   0.02197   0.01370  -0.0326   0.6525   1.0000
   4.500   0.6408   0.02212   0.01354  -0.0283   0.5743   1.0000
   4.750   0.6531   0.02257   0.01355  -0.0239   0.4969   1.0000
   5.000   0.6668   0.02360   0.01399  -0.0202   0.4222   1.0000
   5.250   0.6817   0.02499   0.01495  -0.0173   0.3589   1.0000
   5.500   0.6977   0.02636   0.01604  -0.0148   0.3112   1.0000
   5.750   0.7155   0.02770   0.01716  -0.0126   0.2757   1.0000
   6.000   0.7348   0.02919   0.01860  -0.0108   0.2495   1.0000
   6.250   0.7548   0.03068   0.01997  -0.0092   0.2283   1.0000
   6.500   0.7752   0.03245   0.02177  -0.0077   0.2127   1.0000
   6.750   0.7918   0.03414   0.02362  -0.0056   0.1987   1.0000
   7.000   0.8060   0.03622   0.02601  -0.0031   0.1885   1.0000
   7.250   0.8218   0.03836   0.02826  -0.0011   0.1792   1.0000
   7.500   0.8333   0.04041   0.03060   0.0016   0.1704   1.0000
   7.750   0.8438   0.04312   0.03354   0.0042   0.1648   1.0000
   8.000   0.8445   0.04583   0.03674   0.0082   0.1600   1.0000
   8.250   0.8640   0.04830   0.03905   0.0092   0.1522   1.0000
   8.500   0.8568   0.05152   0.04279   0.0138   0.1505   1.0000
   8.750   0.8463   0.05497   0.04667   0.0182   0.1492   1.0000
   9.000   0.8327   0.05858   0.05062   0.0223   0.1483   1.0000
   9.250   0.8149   0.06235   0.05466   0.0262   0.1478   1.0000
   9.500   0.7955   0.06638   0.05887   0.0296   0.1486   1.0000
   9.750   0.7742   0.07051   0.06311   0.0326   0.1496   1.0000
  10.000   0.7544   0.07470   0.06733   0.0351   0.1508   1.0000
  10.250   0.7360   0.07917   0.07185   0.0367   0.1527   1.0000
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