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S9027 (8%) (s9027-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S9027 (8%) (s9027-il)
Reynolds number: 500,000
Max Cl/Cd: 57.89 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9027-il-500000.txt
Download as CSV file: xf-s9027-il-500000.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 =     0.500 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -1.0148   0.05721   0.05432  -0.0176   1.0000   0.0126
 -12.500  -1.0392   0.04931   0.04621  -0.0242   1.0000   0.0124
 -12.250  -1.0548   0.04452   0.04123  -0.0271   1.0000   0.0125
 -12.000  -1.0620   0.04179   0.03832  -0.0273   1.0000   0.0127
 -11.750  -1.0714   0.03937   0.03572  -0.0256   1.0000   0.0128
 -11.500  -1.0919   0.03527   0.03128  -0.0228   1.0000   0.0130
 -11.250  -1.0996   0.03135   0.02704  -0.0206   1.0000   0.0136
 -11.000  -1.0879   0.02979   0.02537  -0.0195   1.0000   0.0142
 -10.750  -1.0706   0.02892   0.02444  -0.0187   1.0000   0.0149
 -10.500  -1.0528   0.02801   0.02340  -0.0178   1.0000   0.0157
 -10.250  -1.0345   0.02698   0.02223  -0.0169   1.0000   0.0167
 -10.000  -1.0145   0.02618   0.02127  -0.0161   1.0000   0.0175
  -9.750  -0.9967   0.02477   0.01963  -0.0151   1.0000   0.0182
  -9.500  -0.9849   0.02186   0.01646  -0.0136   1.0000   0.0194
  -9.250  -0.9639   0.02095   0.01548  -0.0129   1.0000   0.0204
  -9.000  -0.9415   0.02026   0.01471  -0.0122   1.0000   0.0215
  -8.750  -0.9187   0.01959   0.01392  -0.0115   1.0000   0.0228
  -8.500  -0.8957   0.01887   0.01310  -0.0108   1.0000   0.0238
  -8.250  -0.8722   0.01819   0.01230  -0.0101   1.0000   0.0244
  -8.000  -0.8527   0.01660   0.01054  -0.0090   1.0000   0.0258
  -7.750  -0.8309   0.01561   0.00949  -0.0081   1.0000   0.0275
  -7.500  -0.8073   0.01498   0.00881  -0.0074   1.0000   0.0290
  -7.250  -0.7835   0.01438   0.00814  -0.0067   1.0000   0.0306
  -7.000  -0.7590   0.01390   0.00758  -0.0060   1.0000   0.0324
  -6.750  -0.7358   0.01317   0.00677  -0.0051   1.0000   0.0346
  -6.500  -0.7126   0.01248   0.00607  -0.0043   1.0000   0.0385
  -6.250  -0.6878   0.01209   0.00563  -0.0036   1.0000   0.0425
  -6.000  -0.6642   0.01147   0.00502  -0.0028   1.0000   0.0495
  -5.750  -0.6392   0.01117   0.00467  -0.0022   1.0000   0.0557
  -5.500  -0.6151   0.01071   0.00425  -0.0014   1.0000   0.0654
  -5.250  -0.5907   0.01034   0.00392  -0.0007   1.0000   0.0748
  -5.000  -0.5661   0.01003   0.00362   0.0000   1.0000   0.0848
  -4.750  -0.5416   0.00971   0.00333   0.0007   1.0000   0.0969
  -4.500  -0.5172   0.00939   0.00308   0.0015   1.0000   0.1121
  -4.250  -0.4929   0.00908   0.00285   0.0022   1.0000   0.1312
  -4.000  -0.4686   0.00878   0.00265   0.0029   1.0000   0.1542
  -3.750  -0.4443   0.00849   0.00247   0.0036   1.0000   0.1799
  -3.250  -0.3958   0.00796   0.00214   0.0051   1.0000   0.2336
  -3.000  -0.3718   0.00769   0.00201   0.0059   1.0000   0.2665
  -2.750  -0.3479   0.00743   0.00189   0.0067   1.0000   0.3026
  -2.500  -0.3242   0.00720   0.00180   0.0075   1.0000   0.3391
  -2.250  -0.3005   0.00697   0.00173   0.0084   1.0000   0.3785
  -2.000  -0.2774   0.00674   0.00168   0.0093   1.0000   0.4245
  -1.750  -0.2459   0.00648   0.00165   0.0084   0.9974   0.4832
  -1.500  -0.2057   0.00617   0.00163   0.0057   0.9911   0.5559
  -1.250  -0.1657   0.00591   0.00161   0.0032   0.9839   0.6150
  -1.000  -0.1283   0.00564   0.00158   0.0013   0.9740   0.6762
  -0.750  -0.0926   0.00539   0.00155   0.0000   0.9596   0.7315
  -0.500  -0.0578   0.00517   0.00153  -0.0010   0.9411   0.7863
  -0.250  -0.0269   0.00500   0.00150  -0.0010   0.9141   0.8373
   0.000   0.0000   0.00494   0.00149   0.0000   0.8786   0.8789
   0.250   0.0269   0.00500   0.00150   0.0010   0.8374   0.9141
   0.500   0.0578   0.00517   0.00153   0.0010   0.7864   0.9412
   0.750   0.0925   0.00539   0.00155   0.0000   0.7313   0.9596
   1.000   0.1283   0.00564   0.00158  -0.0013   0.6761   0.9740
   1.250   0.1657   0.00591   0.00161  -0.0032   0.6154   0.9839
   1.500   0.2058   0.00617   0.00163  -0.0057   0.5559   0.9912
   1.750   0.2460   0.00647   0.00165  -0.0084   0.4834   0.9975
   2.000   0.2770   0.00674   0.00168  -0.0092   0.4242   1.0000
   2.250   0.3002   0.00697   0.00173  -0.0083   0.3786   1.0000
   2.500   0.3238   0.00719   0.00180  -0.0074   0.3394   1.0000
   2.750   0.3475   0.00743   0.00189  -0.0066   0.3027   1.0000
   3.000   0.3714   0.00768   0.00201  -0.0058   0.2667   1.0000
   3.250   0.3954   0.00796   0.00214  -0.0050   0.2338   1.0000
   3.500   0.4196   0.00822   0.00229  -0.0043   0.2059   1.0000
   3.750   0.4439   0.00848   0.00246  -0.0035   0.1802   1.0000
   4.000   0.4681   0.00877   0.00265  -0.0028   0.1545   1.0000
   4.250   0.4924   0.00908   0.00285  -0.0021   0.1314   1.0000
   4.500   0.5168   0.00939   0.00307  -0.0014   0.1122   1.0000
   4.750   0.5412   0.00971   0.00333  -0.0006   0.0970   1.0000
   5.000   0.5657   0.01002   0.00362   0.0001   0.0850   1.0000
   5.250   0.5903   0.01034   0.00392   0.0008   0.0747   1.0000
   5.500   0.6148   0.01070   0.00425   0.0015   0.0654   1.0000
   5.750   0.6389   0.01116   0.00466   0.0022   0.0558   1.0000
   6.000   0.6640   0.01147   0.00502   0.0028   0.0495   1.0000
   6.250   0.6876   0.01209   0.00563   0.0037   0.0425   1.0000
   6.500   0.7125   0.01248   0.00607   0.0043   0.0384   1.0000
   6.750   0.7357   0.01320   0.00680   0.0051   0.0344   1.0000
   7.000   0.7591   0.01389   0.00757   0.0060   0.0323   1.0000
   7.250   0.7836   0.01438   0.00813   0.0066   0.0306   1.0000
   7.500   0.8075   0.01497   0.00881   0.0073   0.0290   1.0000
   7.750   0.8312   0.01561   0.00949   0.0080   0.0275   1.0000
   8.000   0.8531   0.01659   0.01054   0.0089   0.0259   1.0000
   8.250   0.8726   0.01822   0.01233   0.0100   0.0245   1.0000
   8.500   0.8962   0.01889   0.01311   0.0107   0.0238   1.0000
   8.750   0.9192   0.01963   0.01396   0.0114   0.0228   1.0000
   9.000   0.9421   0.02032   0.01477   0.0121   0.0215   1.0000
   9.250   0.9647   0.02096   0.01548   0.0127   0.0204   1.0000
   9.500   0.9859   0.02187   0.01646   0.0134   0.0194   1.0000
   9.750   0.9967   0.02504   0.01993   0.0150   0.0181   1.0000
  10.000   1.0155   0.02622   0.02132   0.0159   0.0175   1.0000
  10.250   1.0358   0.02699   0.02223   0.0167   0.0166   1.0000
  10.500   1.0549   0.02785   0.02322   0.0175   0.0156   1.0000
  10.750   1.0728   0.02875   0.02425   0.0183   0.0148   1.0000
  11.000   1.0890   0.02982   0.02540   0.0193   0.0142   1.0000
  11.250   1.1005   0.03143   0.02712   0.0204   0.0136   1.0000
  11.500   1.0917   0.03550   0.03153   0.0226   0.0130   1.0000
  11.750   1.0744   0.03927   0.03562   0.0253   0.0127   1.0000
  12.000   1.0689   0.04128   0.03781   0.0269   0.0126   1.0000
  12.250   1.0465   0.04579   0.04253   0.0263   0.0127   1.0000
  12.500   1.0406   0.04940   0.04631   0.0238   0.0124   1.0000
  12.750   1.0137   0.05784   0.05496   0.0168   0.0126   1.0000
  13.000   0.9791   0.06926   0.06656   0.0077   0.0128   1.0000
  13.250   0.8829   0.09779   0.09552  -0.0117   0.0146   1.0000
  13.500   0.9033   0.09708   0.09476  -0.0111   0.0140   1.0000
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