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S2027 (s2027-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: S2027 (s2027-il)
Reynolds number: 500,000
Max Cl/Cd: 99.61 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s2027-il-500000.txt
Download as CSV file: xf-s2027-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2027                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.000  -0.4192   0.09014   0.08799  -0.0434   1.0000   0.0299
 -10.750  -0.4227   0.08517   0.08305  -0.0461   1.0000   0.0305
  -9.250  -0.6022   0.03147   0.02721  -0.0725   0.9158   0.0205
  -9.000  -0.5970   0.02812   0.02349  -0.0704   0.9034   0.0196
  -8.750  -0.5827   0.02642   0.02153  -0.0689   0.8931   0.0199
  -8.500  -0.5672   0.02445   0.01928  -0.0674   0.8836   0.0198
  -8.250  -0.5489   0.02249   0.01705  -0.0662   0.8740   0.0196
  -8.000  -0.5288   0.02095   0.01528  -0.0651   0.8658   0.0196
  -7.750  -0.5068   0.01968   0.01384  -0.0643   0.8568   0.0197
  -7.500  -0.4844   0.01859   0.01261  -0.0635   0.8486   0.0199
  -7.250  -0.4614   0.01765   0.01154  -0.0627   0.8401   0.0201
  -7.000  -0.4379   0.01682   0.01061  -0.0621   0.8319   0.0204
  -6.750  -0.4145   0.01605   0.00972  -0.0613   0.8237   0.0207
  -6.500  -0.3904   0.01537   0.00895  -0.0608   0.8152   0.0210
  -6.250  -0.3663   0.01479   0.00827  -0.0601   0.8074   0.0213
  -6.000  -0.3430   0.01399   0.00740  -0.0595   0.7986   0.0219
  -5.750  -0.3200   0.01322   0.00655  -0.0588   0.7909   0.0230
  -5.500  -0.2949   0.01270   0.00597  -0.0584   0.7820   0.0239
  -5.250  -0.2693   0.01229   0.00548  -0.0581   0.7742   0.0248
  -5.000  -0.2430   0.01192   0.00503  -0.0578   0.7656   0.0261
  -4.750  -0.2164   0.01161   0.00464  -0.0575   0.7575   0.0274
  -4.500  -0.1900   0.01122   0.00418  -0.0572   0.7492   0.0306
  -4.250  -0.1633   0.01087   0.00383  -0.0570   0.7408   0.0393
  -4.000  -0.1399   0.00998   0.00335  -0.0567   0.7329   0.1315
  -3.750  -0.1150   0.00931   0.00306  -0.0566   0.7243   0.2239
  -3.500  -0.0893   0.00887   0.00283  -0.0564   0.7165   0.2998
  -3.250  -0.0629   0.00848   0.00268  -0.0564   0.7077   0.3691
  -3.000  -0.0362   0.00823   0.00256  -0.0562   0.6998   0.4259
  -2.750  -0.0088   0.00805   0.00248  -0.0562   0.6911   0.4704
  -2.500   0.0187   0.00794   0.00243  -0.0561   0.6831   0.5107
  -2.250   0.0462   0.00786   0.00241  -0.0560   0.6746   0.5485
  -2.000   0.0740   0.00783   0.00241  -0.0559   0.6664   0.5791
  -1.750   0.1020   0.00783   0.00238  -0.0558   0.6582   0.5986
  -1.500   0.1303   0.00782   0.00236  -0.0558   0.6497   0.6144
  -1.250   0.1584   0.00785   0.00233  -0.0558   0.6419   0.6289
  -1.000   0.1867   0.00784   0.00233  -0.0558   0.6333   0.6424
  -0.750   0.2148   0.00788   0.00231  -0.0558   0.6256   0.6549
  -0.500   0.2433   0.00789   0.00230  -0.0558   0.6171   0.6672
  -0.250   0.2713   0.00792   0.00231  -0.0558   0.6093   0.6787
   0.000   0.2994   0.00792   0.00232  -0.0558   0.6009   0.6898
   0.250   0.3275   0.00796   0.00232  -0.0558   0.5932   0.7010
   0.750   0.3836   0.00801   0.00237  -0.0558   0.5772   0.7232
   1.000   0.4114   0.00805   0.00239  -0.0558   0.5691   0.7341
   1.250   0.4394   0.00808   0.00243  -0.0558   0.5614   0.7457
   1.500   0.4671   0.00814   0.00247  -0.0557   0.5535   0.7578
   1.750   0.4947   0.00816   0.00253  -0.0557   0.5455   0.7699
   2.000   0.5219   0.00822   0.00258  -0.0555   0.5378   0.7827
   2.250   0.5493   0.00824   0.00265  -0.0554   0.5297   0.7965
   2.500   0.5761   0.00832   0.00272  -0.0552   0.5221   0.8113
   2.750   0.6030   0.00833   0.00280  -0.0550   0.5138   0.8273
   3.000   0.6291   0.00841   0.00289  -0.0546   0.5063   0.8451
   3.250   0.6551   0.00843   0.00298  -0.0542   0.4980   0.8651
   3.500   0.6796   0.00849   0.00307  -0.0534   0.4904   0.8875
   3.750   0.7039   0.00851   0.00317  -0.0525   0.4821   0.9145
   4.000   0.7309   0.00857   0.00326  -0.0522   0.4742   0.9452
   4.250   0.7680   0.00867   0.00336  -0.0542   0.4649   0.9726
   4.500   0.8093   0.00879   0.00347  -0.0573   0.4555   0.9972
   4.750   0.8360   0.00898   0.00360  -0.0574   0.4471   1.0000
   5.000   0.8622   0.00910   0.00373  -0.0572   0.4382   1.0000
   5.250   0.8879   0.00929   0.00388  -0.0570   0.4299   1.0000
   5.500   0.9139   0.00946   0.00404  -0.0569   0.4209   1.0000
   5.750   0.9399   0.00964   0.00421  -0.0567   0.4122   1.0000
   6.250   0.9912   0.01003   0.00458  -0.0562   0.3940   1.0000
   6.500   1.0164   0.01026   0.00480  -0.0560   0.3851   1.0000
   6.750   1.0415   0.01049   0.00501  -0.0557   0.3759   1.0000
   7.000   1.0668   0.01071   0.00524  -0.0554   0.3669   1.0000
   7.250   1.0909   0.01099   0.00550  -0.0550   0.3579   1.0000
   7.500   1.1156   0.01122   0.00575  -0.0546   0.3477   1.0000
   7.750   1.1396   0.01148   0.00602  -0.0542   0.3367   1.0000
   8.000   1.1628   0.01179   0.00630  -0.0536   0.3257   1.0000
   8.250   1.1851   0.01212   0.00661  -0.0529   0.3133   1.0000
   8.500   1.2070   0.01247   0.00694  -0.0522   0.3006   1.0000
   8.750   1.2293   0.01278   0.00726  -0.0515   0.2888   1.0000
   9.000   1.2504   0.01315   0.00762  -0.0507   0.2761   1.0000
   9.250   1.2703   0.01356   0.00801  -0.0497   0.2630   1.0000
   9.500   1.2890   0.01401   0.00843  -0.0485   0.2492   1.0000
   9.750   1.3058   0.01451   0.00891  -0.0470   0.2338   1.0000
  10.000   1.3189   0.01507   0.00941  -0.0450   0.2178   1.0000
  10.250   1.3294   0.01570   0.00999  -0.0425   0.2019   1.0000
  10.500   1.3383   0.01645   0.01068  -0.0401   0.1853   1.0000
  10.750   1.3477   0.01725   0.01143  -0.0379   0.1692   1.0000
  11.000   1.3551   0.01819   0.01231  -0.0356   0.1521   1.0000
  11.250   1.3601   0.01933   0.01338  -0.0332   0.1346   1.0000
  11.500   1.3635   0.02064   0.01462  -0.0310   0.1179   1.0000
  11.750   1.3661   0.02211   0.01602  -0.0288   0.1005   1.0000
  12.000   1.3667   0.02379   0.01763  -0.0268   0.0846   1.0000
  12.250   1.3670   0.02560   0.01938  -0.0250   0.0716   1.0000
  12.500   1.3685   0.02744   0.02120  -0.0235   0.0615   1.0000
  12.750   1.3672   0.02960   0.02333  -0.0221   0.0508   1.0000
  13.000   1.3675   0.03172   0.02547  -0.0210   0.0432   1.0000
  13.250   1.3663   0.03409   0.02783  -0.0200   0.0364   1.0000
  13.500   1.3614   0.03692   0.03066  -0.0192   0.0290   1.0000
  13.750   1.3538   0.04014   0.03389  -0.0185   0.0233   1.0000
  14.000   1.3522   0.04291   0.03673  -0.0182   0.0204   1.0000
  14.250   1.3434   0.04659   0.04046  -0.0181   0.0177   1.0000
  14.500   1.3431   0.04949   0.04347  -0.0182   0.0169   1.0000
  14.750   1.3399   0.05282   0.04689  -0.0184   0.0156   1.0000
  15.000   1.3342   0.05656   0.05071  -0.0189   0.0147   1.0000
  15.250   1.3261   0.06075   0.05499  -0.0197   0.0140   1.0000
  15.500   1.3170   0.06523   0.05958  -0.0207   0.0136   1.0000
  15.750   1.3149   0.06888   0.06334  -0.0216   0.0132   1.0000
  16.000   1.3099   0.07302   0.06759  -0.0227   0.0129   1.0000
  16.250   1.3068   0.07698   0.07165  -0.0239   0.0123   1.0000
  16.500   1.3017   0.08133   0.07609  -0.0253   0.0118   1.0000
  16.750   1.2957   0.08587   0.08073  -0.0268   0.0117   1.0000
  17.000   1.2893   0.09060   0.08555  -0.0285   0.0114   1.0000
  17.250   1.2813   0.09567   0.09071  -0.0305   0.0111   1.0000
  17.500   1.2725   0.10091   0.09604  -0.0325   0.0108   1.0000
  17.750   1.2640   0.10619   0.10141  -0.0347   0.0106   1.0000
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