Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

S8038 (13%) (s8038-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S8038 (13%) (s8038-il)
Reynolds number: 200,000
Max Cl/Cd: 59.8 at α=5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s8038-il-200000.txt
Download as CSV file: xf-s8038-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8038 (13%)                                     
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -14.500  -0.3986   0.14448   0.14082  -0.0149   1.0000   0.0563
 -14.250  -0.5573   0.15024   0.14628  -0.0128   1.0000   0.0537
 -14.000  -0.5406   0.14833   0.14435  -0.0108   1.0000   0.0549
 -13.750  -0.5313   0.14561   0.14163  -0.0107   1.0000   0.0562
 -13.500  -0.5261   0.14224   0.13827  -0.0116   1.0000   0.0577
 -13.250  -0.5238   0.13845   0.13448  -0.0131   1.0000   0.0597
 -13.000  -0.5500   0.13040   0.12653  -0.0217   1.0000   0.0637
 -12.750  -0.5617   0.12301   0.11920  -0.0253   1.0000   0.0644
 -12.500  -0.5471   0.12089   0.11706  -0.0228   1.0000   0.0653
 -12.250  -0.5005   0.09026   0.08664  -0.0395   1.0000   0.0430
 -12.000  -0.5035   0.08603   0.08245  -0.0398   1.0000   0.0416
 -11.750  -0.4994   0.08605   0.08253  -0.0408   1.0000   0.0546
 -11.500  -0.4754   0.08874   0.08522  -0.0371   1.0000   0.0561
 -11.250  -0.7208   0.04912   0.04460  -0.0575   1.0000   0.0361
 -11.000  -0.7178   0.04532   0.04076  -0.0566   1.0000   0.0349
 -10.750  -0.8086   0.05416   0.04923  -0.0494   1.0000   0.0351
 -10.500  -0.8188   0.05045   0.04542  -0.0465   1.0000   0.0343
 -10.250  -0.8301   0.04715   0.04192  -0.0432   1.0000   0.0337
 -10.000  -0.8388   0.04390   0.03841  -0.0396   1.0000   0.0331
  -9.750  -0.8451   0.04055   0.03473  -0.0359   1.0000   0.0323
  -9.500  -0.8467   0.03737   0.03117  -0.0323   1.0000   0.0317
  -9.250  -0.8423   0.03479   0.02826  -0.0293   1.0000   0.0316
  -9.000  -0.8337   0.03255   0.02573  -0.0266   1.0000   0.0315
  -8.750  -0.8215   0.03081   0.02377  -0.0243   1.0000   0.0321
  -8.500  -0.8081   0.02950   0.02229  -0.0220   1.0000   0.0333
  -8.250  -0.7935   0.02801   0.02060  -0.0199   1.0000   0.0340
  -8.000  -0.7773   0.02649   0.01889  -0.0179   1.0000   0.0344
  -7.750  -0.7604   0.02515   0.01741  -0.0159   1.0000   0.0348
  -7.500  -0.7434   0.02405   0.01618  -0.0139   1.0000   0.0354
  -7.250  -0.7272   0.02254   0.01463  -0.0120   1.0000   0.0362
  -7.000  -0.7135   0.02132   0.01345  -0.0097   1.0000   0.0375
  -6.750  -0.7002   0.02051   0.01266  -0.0073   1.0000   0.0389
  -6.500  -0.6873   0.01984   0.01198  -0.0048   1.0000   0.0410
  -6.250  -0.6737   0.01936   0.01141  -0.0023   1.0000   0.0436
  -6.000  -0.6655   0.01835   0.01047   0.0007   1.0000   0.0464
  -5.750  -0.6542   0.01780   0.00991   0.0033   1.0000   0.0498
  -5.500  -0.6247   0.01683   0.00898   0.0024   0.9959   0.0615
  -5.250  -0.5913   0.01534   0.00792   0.0003   0.9890   0.1207
  -5.000  -0.5546   0.01433   0.00740  -0.0025   0.9829   0.2112
  -4.750  -0.5211   0.01355   0.00698  -0.0044   0.9744   0.2893
  -4.500  -0.4885   0.01279   0.00667  -0.0059   0.9661   0.3830
  -4.250  -0.4531   0.01219   0.00650  -0.0077   0.9592   0.4768
  -4.000  -0.4208   0.01191   0.00641  -0.0085   0.9499   0.5376
  -3.750  -0.3803   0.01175   0.00634  -0.0107   0.9446   0.5854
  -3.500  -0.3468   0.01165   0.00624  -0.0115   0.9354   0.6165
  -3.250  -0.3052   0.01153   0.00612  -0.0139   0.9306   0.6441
  -3.000  -0.2690   0.01145   0.00603  -0.0152   0.9225   0.6666
  -2.750  -0.2291   0.01135   0.00587  -0.0172   0.9160   0.6868
  -2.500  -0.1934   0.01125   0.00576  -0.0184   0.9072   0.7036
  -2.250  -0.1547   0.01115   0.00563  -0.0201   0.8994   0.7199
  -2.000  -0.1223   0.01108   0.00555  -0.0205   0.8880   0.7341
  -1.750  -0.0877   0.01101   0.00546  -0.0214   0.8776   0.7463
  -1.500  -0.0542   0.01094   0.00535  -0.0220   0.8668   0.7583
  -1.250  -0.0264   0.01092   0.00530  -0.0216   0.8535   0.7706
  -1.000   0.0010   0.01091   0.00524  -0.0211   0.8405   0.7831
  -0.750   0.0298   0.01091   0.00522  -0.0208   0.8282   0.7931
  -0.500   0.0580   0.01090   0.00517  -0.0205   0.8162   0.8037
  -0.250   0.0843   0.01090   0.00511  -0.0198   0.8038   0.8153
   0.000   0.1106   0.01092   0.00512  -0.0190   0.7905   0.8254
   0.250   0.1365   0.01092   0.00511  -0.0183   0.7774   0.8357
   0.500   0.1618   0.01093   0.00507  -0.0174   0.7645   0.8470
   0.750   0.1894   0.01095   0.00507  -0.0169   0.7520   0.8568
   1.000   0.2167   0.01097   0.00504  -0.0164   0.7396   0.8672
   1.250   0.2416   0.01097   0.00505  -0.0155   0.7259   0.8790
   1.500   0.2698   0.01101   0.00507  -0.0152   0.7118   0.8894
   1.750   0.2989   0.01104   0.00507  -0.0151   0.6967   0.8995
   2.000   0.3274   0.01107   0.00507  -0.0149   0.6811   0.9108
   2.250   0.3618   0.01114   0.00512  -0.0159   0.6651   0.9195
   2.500   0.3958   0.01122   0.00517  -0.0169   0.6489   0.9286
   2.750   0.4320   0.01131   0.00523  -0.0185   0.6318   0.9372
   3.000   0.4705   0.01142   0.00528  -0.0205   0.6140   0.9443
   3.250   0.5100   0.01153   0.00538  -0.0228   0.5937   0.9513
   3.500   0.5485   0.01164   0.00545  -0.0249   0.5715   0.9585
   3.750   0.5879   0.01177   0.00553  -0.0273   0.5471   0.9659
   4.000   0.6263   0.01191   0.00558  -0.0295   0.5196   0.9738
   4.250   0.6638   0.01207   0.00567  -0.0317   0.4896   0.9830
   4.500   0.7046   0.01224   0.00576  -0.0347   0.4539   0.9906
   4.750   0.7447   0.01250   0.00585  -0.0377   0.4111   0.9985
   5.000   0.7594   0.01270   0.00592  -0.0357   0.3761   1.0000
   5.250   0.7666   0.01297   0.00605  -0.0322   0.3446   1.0000
   5.500   0.7748   0.01333   0.00625  -0.0288   0.3116   1.0000
   5.750   0.7848   0.01379   0.00653  -0.0257   0.2790   1.0000
   6.000   0.7963   0.01432   0.00688  -0.0229   0.2497   1.0000
   6.250   0.8088   0.01490   0.00729  -0.0202   0.2254   1.0000
   6.500   0.8230   0.01545   0.00774  -0.0178   0.2047   1.0000
   6.750   0.8374   0.01604   0.00822  -0.0155   0.1883   1.0000
   7.000   0.8524   0.01664   0.00874  -0.0133   0.1749   1.0000
   7.250   0.8672   0.01727   0.00930  -0.0111   0.1635   1.0000
   7.500   0.8820   0.01796   0.00989  -0.0089   0.1536   1.0000
   7.750   0.8995   0.01848   0.01046  -0.0071   0.1451   1.0000
   8.000   0.9149   0.01930   0.01116  -0.0052   0.1381   1.0000
   8.250   0.9329   0.01979   0.01175  -0.0035   0.1312   1.0000
   8.500   0.9494   0.02060   0.01247  -0.0018   0.1253   1.0000
   8.750   0.9674   0.02121   0.01317  -0.0003   0.1200   1.0000
   9.000   0.9847   0.02182   0.01380   0.0014   0.1149   1.0000
   9.250   1.0029   0.02283   0.01473   0.0026   0.1099   1.0000
   9.500   1.0196   0.02339   0.01545   0.0043   0.1058   1.0000
   9.750   1.0361   0.02403   0.01613   0.0060   0.1016   1.0000
  10.000   1.0565   0.02532   0.01731   0.0066   0.0970   1.0000
  10.250   1.0710   0.02595   0.01813   0.0086   0.0941   1.0000
  10.500   1.0854   0.02668   0.01898   0.0105   0.0906   1.0000
  10.750   1.0994   0.02743   0.01974   0.0124   0.0872   1.0000
  11.000   1.1190   0.02892   0.02123   0.0129   0.0835   1.0000
  11.250   1.1280   0.02970   0.02220   0.0156   0.0810   1.0000
  11.500   1.1389   0.03064   0.02326   0.0178   0.0782   1.0000
  11.750   1.1513   0.03159   0.02425   0.0196   0.0757   1.0000
  12.000   1.1706   0.03330   0.02594   0.0200   0.0727   1.0000
  12.250   1.1772   0.03472   0.02758   0.0223   0.0708   1.0000
  12.500   1.1818   0.03593   0.02899   0.0248   0.0690   1.0000
  12.750   1.1868   0.03725   0.03047   0.0270   0.0670   1.0000
  13.000   1.1926   0.03857   0.03190   0.0289   0.0652   1.0000
  13.250   1.2005   0.03998   0.03337   0.0303   0.0637   1.0000
  13.500   1.2114   0.04182   0.03525   0.0313   0.0621   1.0000
  13.750   1.2115   0.04498   0.03861   0.0327   0.0607   1.0000
  14.000   1.2038   0.04709   0.04097   0.0346   0.0600   1.0000
  14.250   1.1949   0.04965   0.04377   0.0360   0.0592   1.0000
  14.500   1.1841   0.05255   0.04692   0.0369   0.0584   1.0000
  14.750   1.1711   0.05599   0.05058   0.0373   0.0577   1.0000
  15.000   1.1567   0.05978   0.05459   0.0371   0.0570   1.0000
  15.250   1.1391   0.06420   0.05922   0.0362   0.0565   1.0000
  15.500   1.1152   0.06977   0.06501   0.0344   0.0563   1.0000
  15.750   1.0818   0.07711   0.07258   0.0310   0.0562   1.0000
  16.000   1.0246   0.08910   0.08488   0.0241   0.0570   1.0000
<< Back to S8038 (13%) (s8038-il)

Polar data table (+)

Polar graphs


<< Back to S8038 (13%) (s8038-il)