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SD5060 (9.5%) (sd5060-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SD5060 (9.5%) (sd5060-il)
Reynolds number: 50,000
Max Cl/Cd: 36.31 at α=5.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sd5060-il-50000-n5.txt
Download as CSV file: xf-sd5060-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SD5060 (9.5%)                                   
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.4821   0.09493   0.08795  -0.0191   1.0000   0.0549
  -9.000  -0.4838   0.09027   0.08336  -0.0217   1.0000   0.0551
  -8.750  -0.4871   0.08534   0.07852  -0.0247   1.0000   0.0547
  -8.500  -0.4932   0.07993   0.07321  -0.0283   1.0000   0.0542
  -8.250  -0.5042   0.07333   0.06671  -0.0337   1.0000   0.0533
  -8.000  -0.5183   0.06457   0.05792  -0.0415   1.0000   0.0522
  -7.750  -0.5302   0.05707   0.05018  -0.0466   1.0000   0.0514
  -7.500  -0.5319   0.05136   0.04412  -0.0492   1.0000   0.0513
  -7.250  -0.5261   0.04689   0.03932  -0.0502   1.0000   0.0518
  -7.000  -0.5162   0.04308   0.03514  -0.0505   1.0000   0.0525
  -6.750  -0.5036   0.03973   0.03142  -0.0504   1.0000   0.0537
  -6.500  -0.4890   0.03675   0.02804  -0.0498   1.0000   0.0553
  -6.250  -0.4730   0.03420   0.02506  -0.0490   1.0000   0.0583
  -6.000  -0.4558   0.03187   0.02226  -0.0480   1.0000   0.0620
  -5.750  -0.4383   0.03034   0.02068  -0.0469   1.0000   0.0656
  -5.500  -0.4198   0.02863   0.01873  -0.0456   1.0000   0.0695
  -5.250  -0.4006   0.02696   0.01676  -0.0442   1.0000   0.0744
  -5.000  -0.3826   0.02579   0.01560  -0.0429   1.0000   0.0819
  -4.750  -0.3639   0.02471   0.01447  -0.0418   1.0000   0.0950
  -4.500  -0.3444   0.02367   0.01332  -0.0406   1.0000   0.1145
  -4.250  -0.3253   0.02296   0.01269  -0.0397   1.0000   0.1436
  -4.000  -0.3061   0.02245   0.01228  -0.0389   1.0000   0.1782
  -3.750  -0.2861   0.02191   0.01173  -0.0380   1.0000   0.2099
  -3.500  -0.2661   0.02145   0.01124  -0.0371   1.0000   0.2389
  -3.250  -0.2457   0.02106   0.01082  -0.0363   1.0000   0.2688
  -3.000  -0.2107   0.02067   0.01043  -0.0382   0.9922   0.3071
  -2.750  -0.1730   0.02031   0.01011  -0.0405   0.9834   0.3496
  -2.500  -0.1372   0.01995   0.00983  -0.0424   0.9740   0.3966
  -2.250  -0.1013   0.01962   0.00965  -0.0442   0.9649   0.4529
  -2.000  -0.0650   0.01928   0.00956  -0.0458   0.9563   0.5240
  -1.750  -0.0343   0.01894   0.00951  -0.0461   0.9460   0.6059
  -1.500  -0.0041   0.01863   0.00953  -0.0457   0.9366   0.7080
  -1.250   0.0363   0.01834   0.00951  -0.0467   0.9290   0.8486
  -1.000   0.0990   0.01819   0.00917  -0.0534   0.9216   1.0000
  -0.750   0.1389   0.01834   0.00905  -0.0560   0.9117   1.0000
  -0.500   0.1730   0.01850   0.00901  -0.0575   0.8998   1.0000
  -0.250   0.2052   0.01867   0.00899  -0.0584   0.8875   1.0000
   0.000   0.2369   0.01884   0.00902  -0.0592   0.8752   1.0000
   0.250   0.2683   0.01900   0.00906  -0.0598   0.8630   1.0000
   0.500   0.2995   0.01915   0.00910  -0.0603   0.8508   1.0000
   0.750   0.3305   0.01928   0.00914  -0.0605   0.8386   1.0000
   1.000   0.3590   0.01942   0.00922  -0.0603   0.8252   1.0000
   1.250   0.3862   0.01957   0.00931  -0.0598   0.8111   1.0000
   1.500   0.4133   0.01970   0.00940  -0.0593   0.7966   1.0000
   1.750   0.4404   0.01982   0.00948  -0.0586   0.7818   1.0000
   2.000   0.4672   0.01991   0.00955  -0.0578   0.7666   1.0000
   2.250   0.4933   0.01999   0.00961  -0.0569   0.7505   1.0000
   2.500   0.5181   0.02010   0.00973  -0.0558   0.7326   1.0000
   2.750   0.5433   0.02018   0.00983  -0.0546   0.7143   1.0000
   3.000   0.5690   0.02022   0.00986  -0.0534   0.6959   1.0000
   3.250   0.5945   0.02025   0.00988  -0.0522   0.6768   1.0000
   3.500   0.6187   0.02036   0.01004  -0.0509   0.6548   1.0000
   3.750   0.6440   0.02039   0.01006  -0.0496   0.6335   1.0000
   4.000   0.6679   0.02053   0.01022  -0.0483   0.6087   1.0000
   4.250   0.6920   0.02067   0.01036  -0.0470   0.5827   1.0000
   4.500   0.7159   0.02084   0.01054  -0.0457   0.5549   1.0000
   4.750   0.7395   0.02106   0.01074  -0.0443   0.5250   1.0000
   5.000   0.7625   0.02136   0.01098  -0.0430   0.4932   1.0000
   5.250   0.7852   0.02173   0.01127  -0.0417   0.4605   1.0000
   5.500   0.8071   0.02223   0.01173  -0.0404   0.4264   1.0000
   5.750   0.8287   0.02283   0.01223  -0.0392   0.3929   1.0000
   6.000   0.8497   0.02352   0.01282  -0.0381   0.3612   1.0000
   6.250   0.8706   0.02432   0.01352  -0.0370   0.3321   1.0000
   6.500   0.8913   0.02518   0.01433  -0.0360   0.3060   1.0000
   6.750   0.9120   0.02611   0.01521  -0.0350   0.2832   1.0000
   7.000   0.9329   0.02709   0.01620  -0.0342   0.2623   1.0000
   7.250   0.9536   0.02811   0.01719  -0.0333   0.2441   1.0000
   7.500   0.9747   0.02917   0.01825  -0.0324   0.2282   1.0000
   7.750   0.9955   0.03028   0.01936  -0.0316   0.2132   1.0000
   8.000   1.0162   0.03142   0.02062  -0.0308   0.1993   1.0000
   8.250   1.0366   0.03263   0.02196  -0.0299   0.1864   1.0000
   8.500   1.0561   0.03390   0.02337  -0.0291   0.1739   1.0000
   8.750   1.0755   0.03527   0.02490  -0.0282   0.1628   1.0000
   9.000   1.0936   0.03666   0.02641  -0.0272   0.1522   1.0000
   9.250   1.1119   0.03802   0.02780  -0.0263   0.1427   1.0000
   9.500   1.1273   0.03971   0.02983  -0.0252   0.1328   1.0000
   9.750   1.1417   0.04142   0.03173  -0.0241   0.1239   1.0000
  10.000   1.1569   0.04297   0.03331  -0.0231   0.1162   1.0000
  10.250   1.1661   0.04519   0.03593  -0.0217   0.1082   1.0000
  10.500   1.1784   0.04682   0.03753  -0.0205   0.1015   1.0000
  10.750   1.1821   0.04960   0.04079  -0.0189   0.0955   1.0000
  11.000   1.1912   0.05127   0.04245  -0.0177   0.0899   1.0000
  11.250   1.1855   0.05431   0.04593  -0.0158   0.0856   1.0000
  11.500   1.1793   0.05734   0.04925  -0.0143   0.0819   1.0000
  11.750   1.1803   0.05967   0.05165  -0.0132   0.0782   1.0000
  12.000   1.1736   0.06304   0.05518  -0.0126   0.0754   1.0000
  12.250   1.1535   0.06802   0.06052  -0.0130   0.0740   1.0000
  12.500   1.1311   0.07379   0.06657  -0.0147   0.0731   1.0000
  12.750   1.1046   0.08084   0.07387  -0.0178   0.0730   1.0000
  13.000   1.0732   0.08967   0.08289  -0.0227   0.0737   1.0000
  13.250   1.0381   0.10055   0.09384  -0.0294   0.0749   1.0000
  13.500   1.0018   0.11333   0.10666  -0.0374   0.0758   1.0000
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