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S6061 9% (s6061-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S6061 9% (s6061-il)
Reynolds number: 200,000
Max Cl/Cd: 68.21 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s6061-il-200000.txt
Download as CSV file: xf-s6061-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6061 9%                                        
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.4106   0.08466   0.08149  -0.0203   1.0000   0.0500
  -8.750  -0.4234   0.07930   0.07618  -0.0257   1.0000   0.0510
  -8.500  -0.4357   0.07362   0.07054  -0.0310   1.0000   0.0512
  -8.250  -0.4508   0.06791   0.06482  -0.0366   1.0000   0.0513
  -8.000  -0.4658   0.06353   0.06038  -0.0390   1.0000   0.0513
  -7.750  -0.4762   0.05891   0.05563  -0.0409   1.0000   0.0515
  -7.500  -0.4753   0.05138   0.04824  -0.0411   1.0000   0.0529
  -7.250  -0.4655   0.04828   0.04519  -0.0401   1.0000   0.0542
  -7.000  -0.4621   0.04469   0.04159  -0.0401   1.0000   0.0557
  -6.750  -0.4615   0.04092   0.03774  -0.0401   1.0000   0.0575
  -6.500  -0.4650   0.03736   0.03408  -0.0390   1.0000   0.0598
  -6.000  -0.4968   0.04286   0.03857  -0.0368   1.0000   0.0661
  -5.750  -0.4896   0.04051   0.03624  -0.0347   1.0000   0.0677
  -5.500  -0.4676   0.02589   0.02200  -0.0313   0.9990   0.0701
  -5.250  -0.4683   0.02797   0.02189  -0.0276   1.0000   0.0291
  -5.000  -0.4533   0.02491   0.01858  -0.0259   1.0000   0.0275
  -4.750  -0.4173   0.02169   0.01487  -0.0277   0.9961   0.0268
  -4.500  -0.3787   0.02043   0.01321  -0.0297   0.9914   0.0289
  -4.250  -0.3432   0.01776   0.01029  -0.0313   0.9873   0.0302
  -4.000  -0.3047   0.01614   0.00861  -0.0334   0.9836   0.0319
  -3.750  -0.2695   0.01506   0.00750  -0.0349   0.9772   0.0352
  -3.500  -0.2307   0.01390   0.00630  -0.0372   0.9723   0.0461
  -3.250  -0.1965   0.01225   0.00524  -0.0390   0.9663   0.1636
  -3.000  -0.1626   0.01098   0.00497  -0.0413   0.9603   0.3804
  -2.750  -0.1286   0.01005   0.00487  -0.0427   0.9553   0.5897
  -2.500  -0.1003   0.00968   0.00491  -0.0422   0.9471   0.7178
  -2.250  -0.0679   0.00955   0.00490  -0.0422   0.9411   0.7966
  -2.000  -0.0405   0.00952   0.00490  -0.0411   0.9323   0.8465
  -1.750  -0.0128   0.00953   0.00488  -0.0401   0.9241   0.8854
  -1.500   0.0193   0.00953   0.00482  -0.0398   0.9167   0.9163
  -1.250   0.0546   0.00954   0.00473  -0.0405   0.9085   0.9415
  -1.000   0.1009   0.00950   0.00458  -0.0436   0.9024   0.9586
  -0.750   0.1505   0.00944   0.00441  -0.0476   0.8945   0.9722
  -0.500   0.1998   0.00931   0.00417  -0.0517   0.8870   0.9842
  -0.250   0.2492   0.00916   0.00394  -0.0561   0.8763   0.9962
   0.000   0.2771   0.00905   0.00376  -0.0562   0.8632   1.0000
   0.250   0.2955   0.00900   0.00363  -0.0544   0.8492   1.0000
   0.500   0.3144   0.00897   0.00354  -0.0527   0.8354   1.0000
   0.750   0.3341   0.00896   0.00346  -0.0510   0.8217   1.0000
   1.000   0.3545   0.00896   0.00340  -0.0494   0.8080   1.0000
   1.250   0.3756   0.00898   0.00337  -0.0480   0.7942   1.0000
   1.500   0.3974   0.00901   0.00334  -0.0467   0.7802   1.0000
   1.750   0.4199   0.00905   0.00333  -0.0455   0.7661   1.0000
   2.000   0.4429   0.00911   0.00334  -0.0444   0.7517   1.0000
   2.250   0.4663   0.00917   0.00338  -0.0433   0.7368   1.0000
   2.500   0.4902   0.00925   0.00341  -0.0424   0.7214   1.0000
   2.750   0.5144   0.00933   0.00344  -0.0414   0.7052   1.0000
   3.000   0.5390   0.00942   0.00349  -0.0406   0.6885   1.0000
   3.250   0.5637   0.00952   0.00361  -0.0398   0.6696   1.0000
   3.500   0.5886   0.00964   0.00370  -0.0391   0.6504   1.0000
   3.750   0.6135   0.00978   0.00380  -0.0383   0.6304   1.0000
   4.000   0.6385   0.00992   0.00394  -0.0376   0.6077   1.0000
   4.250   0.6633   0.01009   0.00411  -0.0369   0.5832   1.0000
   4.500   0.6880   0.01029   0.00427  -0.0362   0.5566   1.0000
   4.750   0.7124   0.01051   0.00446  -0.0355   0.5261   1.0000
   5.000   0.7360   0.01079   0.00465  -0.0346   0.4878   1.0000
   5.250   0.7587   0.01117   0.00489  -0.0336   0.4394   1.0000
   5.500   0.7808   0.01165   0.00519  -0.0327   0.3867   1.0000
   5.750   0.8018   0.01229   0.00557  -0.0318   0.3267   1.0000
   6.000   0.8229   0.01299   0.00603  -0.0309   0.2696   1.0000
   6.250   0.8440   0.01374   0.00657  -0.0301   0.2156   1.0000
   6.500   0.8634   0.01473   0.00727  -0.0292   0.1485   1.0000
   6.750   0.8747   0.01696   0.00877  -0.0272   0.0547   1.0000
   7.000   0.8916   0.01838   0.01017  -0.0257   0.0420   1.0000
   7.250   0.9117   0.01935   0.01126  -0.0245   0.0378   1.0000
   7.500   0.9304   0.02050   0.01248  -0.0232   0.0350   1.0000
   7.750   0.9474   0.02197   0.01398  -0.0217   0.0328   1.0000
   8.000   0.9641   0.02433   0.01637  -0.0202   0.0313   1.0000
   8.250   0.9859   0.02588   0.01809  -0.0193   0.0304   1.0000
   8.500   1.0075   0.02719   0.01959  -0.0183   0.0288   1.0000
   8.750   1.0287   0.02908   0.02169  -0.0174   0.0277   1.0000
   9.000   1.0489   0.03145   0.02432  -0.0163   0.0272   1.0000
   9.250   1.0667   0.03429   0.02750  -0.0150   0.0270   1.0000
   9.500   1.0800   0.03765   0.03127  -0.0133   0.0272   1.0000
   9.750   1.0889   0.04094   0.03497  -0.0114   0.0270   1.0000
  10.000   1.0951   0.04382   0.03818  -0.0095   0.0262   1.0000
  10.250   1.0960   0.04710   0.04179  -0.0073   0.0258   1.0000
  10.500   1.0854   0.05164   0.04677  -0.0045   0.0267   1.0000
  10.750   1.0681   0.05563   0.05107  -0.0014   0.0275   1.0000
  11.000   1.0489   0.05956   0.05523   0.0007   0.0282   1.0000
  11.250   1.0298   0.06380   0.05967   0.0013   0.0288   1.0000
  11.500   1.0083   0.06860   0.06466   0.0007   0.0291   1.0000
  11.750   0.9874   0.07399   0.07020  -0.0013   0.0295   1.0000
  12.000   0.9660   0.08016   0.07651  -0.0045   0.0298   1.0000
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