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S6063 7.05% (s6063-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: S6063 7.05% (s6063-il)
Reynolds number: 100,000
Max Cl/Cd: 45.33 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s6063-il-100000-n5.txt
Download as CSV file: xf-s6063-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S6063 7.05%                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.250  -0.5563   0.10709   0.10220  -0.0020   1.0000   0.0498
  -9.000  -0.5565   0.10308   0.09824  -0.0054   1.0000   0.0500
  -8.750  -0.5564   0.09888   0.09410  -0.0087   1.0000   0.0501
  -8.500  -0.5401   0.09282   0.08797  -0.0045   1.0000   0.0322
  -8.250  -0.5449   0.08598   0.08120  -0.0100   1.0000   0.0255
  -8.000  -0.5441   0.08212   0.07738  -0.0117   1.0000   0.0247
  -7.750  -0.5451   0.07768   0.07300  -0.0148   1.0000   0.0239
  -7.500  -0.5426   0.07246   0.06779  -0.0196   1.0000   0.0231
  -7.250  -0.5393   0.06634   0.06163  -0.0246   1.0000   0.0221
  -6.750  -0.5268   0.05143   0.04615  -0.0333   1.0000   0.0191
  -6.500  -0.5156   0.04711   0.04160  -0.0345   1.0000   0.0188
  -6.250  -0.5023   0.04286   0.03705  -0.0352   1.0000   0.0185
  -6.000  -0.4868   0.03876   0.03256  -0.0356   1.0000   0.0183
  -5.750  -0.4693   0.03497   0.02833  -0.0355   1.0000   0.0180
  -5.500  -0.4500   0.03160   0.02448  -0.0351   1.0000   0.0178
  -5.250  -0.4289   0.02866   0.02094  -0.0344   1.0000   0.0184
  -5.000  -0.4065   0.02635   0.01808  -0.0335   1.0000   0.0193
  -4.750  -0.3851   0.02412   0.01560  -0.0328   1.0000   0.0204
  -4.500  -0.3626   0.02231   0.01354  -0.0318   1.0000   0.0209
  -4.250  -0.3401   0.02072   0.01175  -0.0307   1.0000   0.0214
  -4.000  -0.3179   0.01937   0.01026  -0.0296   1.0000   0.0221
  -3.750  -0.2960   0.01822   0.00900  -0.0284   1.0000   0.0229
  -3.500  -0.2741   0.01722   0.00783  -0.0273   1.0000   0.0244
  -3.250  -0.2522   0.01642   0.00687  -0.0262   1.0000   0.0262
  -3.000  -0.2302   0.01563   0.00602  -0.0252   1.0000   0.0313
  -2.750  -0.2080   0.01488   0.00528  -0.0242   1.0000   0.0455
  -2.500  -0.1865   0.01373   0.00467  -0.0235   1.0000   0.1477
  -2.250  -0.1662   0.01254   0.00442  -0.0229   1.0000   0.3566
  -2.000  -0.1496   0.01146   0.00444  -0.0207   1.0000   0.6131
  -1.750  -0.1268   0.01097   0.00450  -0.0185   0.9951   0.8027
  -1.500  -0.0765   0.01079   0.00432  -0.0221   0.9920   0.9534
  -1.250  -0.0271   0.01079   0.00404  -0.0268   0.9854   1.0000
  -1.000   0.0129   0.01084   0.00390  -0.0296   0.9757   1.0000
  -0.750   0.0537   0.01090   0.00378  -0.0325   0.9663   1.0000
  -0.500   0.0949   0.01094   0.00368  -0.0354   0.9572   1.0000
  -0.250   0.1319   0.01097   0.00361  -0.0373   0.9452   1.0000
   0.000   0.1674   0.01100   0.00356  -0.0389   0.9323   1.0000
   0.250   0.2014   0.01103   0.00353  -0.0400   0.9183   1.0000
   0.500   0.2335   0.01106   0.00351  -0.0407   0.9035   1.0000
   0.750   0.2637   0.01108   0.00350  -0.0409   0.8878   1.0000
   1.000   0.2910   0.01113   0.00353  -0.0405   0.8696   1.0000
   1.250   0.3181   0.01117   0.00355  -0.0400   0.8510   1.0000
   1.500   0.3448   0.01121   0.00359  -0.0394   0.8322   1.0000
   1.750   0.3701   0.01127   0.00365  -0.0385   0.8106   1.0000
   2.000   0.3957   0.01133   0.00371  -0.0375   0.7888   1.0000
   2.250   0.4207   0.01141   0.00379  -0.0366   0.7643   1.0000
   2.500   0.4457   0.01151   0.00391  -0.0355   0.7377   1.0000
   2.750   0.4706   0.01163   0.00402  -0.0345   0.7089   1.0000
   3.000   0.4953   0.01178   0.00414  -0.0334   0.6775   1.0000
   3.250   0.5200   0.01197   0.00431  -0.0324   0.6425   1.0000
   3.500   0.5445   0.01220   0.00454  -0.0313   0.6041   1.0000
   3.750   0.5680   0.01253   0.00473  -0.0301   0.5533   1.0000
   4.000   0.5895   0.01306   0.00491  -0.0286   0.4697   1.0000
   4.250   0.6116   0.01368   0.00522  -0.0275   0.3896   1.0000
   4.500   0.6325   0.01458   0.00568  -0.0265   0.2878   1.0000
   4.750   0.6526   0.01581   0.00627  -0.0258   0.1675   1.0000
   5.000   0.6724   0.01738   0.00719  -0.0250   0.0607   1.0000
   5.250   0.6942   0.01869   0.00834  -0.0242   0.0363   1.0000
   5.500   0.7175   0.01963   0.00940  -0.0235   0.0290   1.0000
   5.750   0.7397   0.02074   0.01064  -0.0226   0.0257   1.0000
   6.000   0.7619   0.02185   0.01201  -0.0218   0.0243   1.0000
   6.250   0.7834   0.02309   0.01343  -0.0208   0.0232   1.0000
   6.500   0.8047   0.02450   0.01497  -0.0198   0.0224   1.0000
   6.750   0.8262   0.02607   0.01669  -0.0189   0.0218   1.0000
   7.000   0.8481   0.02785   0.01864  -0.0180   0.0213   1.0000
   7.250   0.8700   0.02986   0.02085  -0.0171   0.0210   1.0000
   7.500   0.8914   0.03216   0.02342  -0.0162   0.0207   1.0000
   7.750   0.9112   0.03468   0.02626  -0.0153   0.0204   1.0000
   8.000   0.9278   0.03763   0.02946  -0.0145   0.0196   1.0000
   8.250   0.9419   0.04061   0.03301  -0.0133   0.0189   1.0000
   8.500   0.9533   0.04383   0.03675  -0.0120   0.0185   1.0000
   8.750   0.9605   0.04752   0.04090  -0.0108   0.0184   1.0000
   9.000   0.9631   0.05146   0.04528  -0.0096   0.0184   1.0000
   9.250   0.9612   0.05550   0.04969  -0.0085   0.0185   1.0000
   9.500   0.9541   0.05959   0.05409  -0.0076   0.0185   1.0000
   9.750   0.9411   0.06349   0.05822  -0.0067   0.0186   1.0000
  10.000   0.9247   0.06760   0.06251  -0.0068   0.0187   1.0000
  10.250   0.9077   0.07247   0.06753  -0.0090   0.0188   1.0000
  10.500   0.8902   0.07854   0.07372  -0.0132   0.0189   1.0000
  10.750   0.8737   0.08593   0.08120  -0.0191   0.0190   1.0000
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