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S9027 (8%) (s9027-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 200,000
Max Cl/Cd: 43.35 at α=6.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9027-il-200000-n5.txt
Download as CSV file: xf-s9027-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9027 (8%)                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.8849   0.08379   0.08013   0.0025   1.0000   0.0174
 -12.250  -0.9280   0.06942   0.06564  -0.0079   1.0000   0.0165
 -12.000  -0.9583   0.05871   0.05472  -0.0172   1.0000   0.0162
 -11.750  -0.9836   0.05135   0.04713  -0.0231   1.0000   0.0160
 -11.500  -1.0018   0.04686   0.04241  -0.0248   1.0000   0.0161
 -11.250  -1.0163   0.04357   0.03888  -0.0236   1.0000   0.0163
 -11.000  -1.0215   0.04078   0.03580  -0.0222   1.0000   0.0169
 -10.750  -1.0199   0.03812   0.03279  -0.0210   1.0000   0.0175
 -10.500  -1.0137   0.03570   0.03002  -0.0197   1.0000   0.0180
 -10.250  -1.0068   0.03305   0.02716  -0.0185   1.0000   0.0188
 -10.000  -0.9928   0.03139   0.02534  -0.0175   1.0000   0.0195
  -9.750  -0.9768   0.02991   0.02369  -0.0166   1.0000   0.0203
  -9.500  -0.9590   0.02864   0.02223  -0.0157   1.0000   0.0215
  -9.250  -0.9405   0.02729   0.02066  -0.0149   1.0000   0.0228
  -9.000  -0.9212   0.02588   0.01899  -0.0139   1.0000   0.0238
  -8.750  -0.9011   0.02457   0.01740  -0.0130   1.0000   0.0246
  -8.500  -0.8826   0.02290   0.01563  -0.0120   1.0000   0.0258
  -8.250  -0.8614   0.02193   0.01458  -0.0113   1.0000   0.0273
  -8.000  -0.8390   0.02111   0.01366  -0.0106   1.0000   0.0291
  -7.750  -0.8167   0.02019   0.01261  -0.0098   1.0000   0.0308
  -7.500  -0.7942   0.01929   0.01156  -0.0090   1.0000   0.0325
  -7.250  -0.7722   0.01831   0.01047  -0.0081   1.0000   0.0344
  -7.000  -0.7495   0.01752   0.00963  -0.0073   1.0000   0.0372
  -6.750  -0.7257   0.01691   0.00895  -0.0067   1.0000   0.0410
  -6.500  -0.7022   0.01625   0.00822  -0.0060   1.0000   0.0454
  -6.250  -0.6784   0.01565   0.00759  -0.0053   1.0000   0.0510
  -6.000  -0.6543   0.01511   0.00696  -0.0046   1.0000   0.0567
  -5.750  -0.6302   0.01459   0.00645  -0.0039   1.0000   0.0641
  -5.500  -0.6060   0.01411   0.00598  -0.0033   1.0000   0.0729
  -5.250  -0.5815   0.01370   0.00555  -0.0027   1.0000   0.0828
  -5.000  -0.5571   0.01329   0.00515  -0.0020   1.0000   0.0948
  -4.750  -0.5328   0.01287   0.00477  -0.0014   1.0000   0.1093
  -4.500  -0.5086   0.01247   0.00443  -0.0007   1.0000   0.1254
  -4.250  -0.4842   0.01211   0.00412   0.0000   1.0000   0.1425
  -4.000  -0.4599   0.01178   0.00384   0.0007   1.0000   0.1626
  -3.750  -0.4358   0.01143   0.00357   0.0014   1.0000   0.1848
  -3.500  -0.4116   0.01112   0.00334   0.0021   1.0000   0.2074
  -3.250  -0.3875   0.01082   0.00313   0.0029   1.0000   0.2336
  -3.000  -0.3636   0.01051   0.00295   0.0036   1.0000   0.2648
  -2.750  -0.3399   0.01020   0.00278   0.0044   1.0000   0.3001
  -2.500  -0.3164   0.00989   0.00265   0.0052   1.0000   0.3406
  -2.250  -0.2930   0.00960   0.00254   0.0061   1.0000   0.3842
  -2.000  -0.2698   0.00933   0.00245   0.0070   1.0000   0.4267
  -1.750  -0.2469   0.00908   0.00238   0.0080   1.0000   0.4717
  -1.500  -0.2157   0.00882   0.00236   0.0072   0.9947   0.5249
  -1.250  -0.1782   0.00855   0.00236   0.0052   0.9833   0.5869
  -1.000  -0.1426   0.00828   0.00235   0.0038   0.9686   0.6509
  -0.750  -0.1090   0.00804   0.00236   0.0031   0.9495   0.7099
  -0.500  -0.0731   0.00786   0.00237   0.0019   0.9274   0.7647
  -0.250  -0.0367   0.00773   0.00238   0.0009   0.8990   0.8144
   0.000   0.0000   0.00768   0.00239   0.0000   0.8607   0.8605
   0.250   0.0367   0.00773   0.00238  -0.0009   0.8145   0.8990
   0.500   0.0730   0.00786   0.00237  -0.0019   0.7649   0.9274
   0.750   0.1090   0.00804   0.00236  -0.0031   0.7100   0.9496
   1.000   0.1425   0.00828   0.00235  -0.0038   0.6513   0.9687
   1.250   0.1781   0.00855   0.00236  -0.0052   0.5867   0.9833
   1.500   0.2157   0.00882   0.00236  -0.0072   0.5248   0.9947
   1.750   0.2466   0.00908   0.00238  -0.0079   0.4716   1.0000
   2.000   0.2696   0.00933   0.00245  -0.0070   0.4268   1.0000
   2.250   0.2928   0.00960   0.00254  -0.0060   0.3840   1.0000
   2.500   0.3160   0.00989   0.00264  -0.0052   0.3405   1.0000
   2.750   0.3396   0.01020   0.00278  -0.0043   0.3003   1.0000
   3.000   0.3633   0.01051   0.00295  -0.0036   0.2647   1.0000
   3.250   0.3872   0.01082   0.00313  -0.0028   0.2339   1.0000
   3.500   0.4113   0.01112   0.00333  -0.0021   0.2075   1.0000
   3.750   0.4355   0.01143   0.00357  -0.0013   0.1849   1.0000
   4.000   0.4596   0.01178   0.00384  -0.0006   0.1628   1.0000
   4.250   0.4839   0.01211   0.00412   0.0001   0.1426   1.0000
   4.500   0.5083   0.01247   0.00443   0.0007   0.1255   1.0000
   4.750   0.5326   0.01287   0.00477   0.0014   0.1093   1.0000
   5.000   0.5569   0.01329   0.00515   0.0021   0.0949   1.0000
   5.250   0.5813   0.01370   0.00555   0.0027   0.0829   1.0000
   5.500   0.6059   0.01411   0.00598   0.0033   0.0730   1.0000
   5.750   0.6302   0.01459   0.00644   0.0040   0.0641   1.0000
   6.000   0.6543   0.01511   0.00696   0.0046   0.0566   1.0000
   6.250   0.6784   0.01565   0.00759   0.0053   0.0510   1.0000
   6.500   0.7022   0.01625   0.00822   0.0059   0.0454   1.0000
   6.750   0.7258   0.01691   0.00894   0.0067   0.0409   1.0000
   7.000   0.7496   0.01752   0.00964   0.0073   0.0372   1.0000
   7.250   0.7724   0.01832   0.01047   0.0081   0.0344   1.0000
   7.500   0.7944   0.01930   0.01157   0.0089   0.0325   1.0000
   7.750   0.8170   0.02020   0.01261   0.0097   0.0309   1.0000
   8.000   0.8394   0.02111   0.01366   0.0105   0.0291   1.0000
   8.250   0.8618   0.02194   0.01459   0.0112   0.0273   1.0000
   8.500   0.8831   0.02291   0.01563   0.0119   0.0257   1.0000
   8.750   0.9017   0.02458   0.01741   0.0129   0.0246   1.0000
   9.000   0.9220   0.02589   0.01900   0.0138   0.0238   1.0000
   9.250   0.9412   0.02731   0.02067   0.0147   0.0227   1.0000
   9.500   0.9599   0.02865   0.02224   0.0156   0.0214   1.0000
   9.750   0.9778   0.02993   0.02370   0.0164   0.0203   1.0000
  10.000   0.9939   0.03144   0.02539   0.0173   0.0195   1.0000
  10.250   1.0081   0.03305   0.02714   0.0182   0.0188   1.0000
  10.500   1.0147   0.03580   0.03011   0.0194   0.0179   1.0000
  10.750   1.0217   0.03811   0.03278   0.0206   0.0174   1.0000
  11.000   1.0230   0.04082   0.03585   0.0219   0.0168   1.0000
  11.250   1.0177   0.04366   0.03898   0.0233   0.0162   1.0000
  11.500   1.0027   0.04702   0.04258   0.0244   0.0160   1.0000
  11.750   0.9839   0.05161   0.04741   0.0226   0.0159   1.0000
  12.000   0.9602   0.05879   0.05480   0.0168   0.0161   1.0000
  12.250   0.9254   0.07039   0.06661   0.0070   0.0169   1.0000
  12.500   0.8845   0.08444   0.08078  -0.0033   0.0175   1.0000
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