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S8037 (16%) (s8037-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S8037 (16%) (s8037-il)
Reynolds number: 50,000
Max Cl/Cd: 22.82 at α=9.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s8037-il-50000-n5.txt
Download as CSV file: xf-s8037-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S8037 (16%)                                     
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -11.750  -0.3969   0.10450   0.09722  -0.0543   1.0000   0.0516
 -11.500  -0.4056   0.09869   0.09149  -0.0568   1.0000   0.0514
 -11.250  -0.4211   0.09153   0.08438  -0.0603   1.0000   0.0510
 -11.000  -0.4423   0.08448   0.07736  -0.0641   1.0000   0.0504
 -10.750  -0.4710   0.07785   0.07076  -0.0674   1.0000   0.0499
 -10.500  -0.5011   0.07261   0.06549  -0.0688   1.0000   0.0492
 -10.250  -0.5313   0.06856   0.06141  -0.0681   1.0000   0.0483
 -10.000  -0.5615   0.06577   0.05859  -0.0651   1.0000   0.0481
  -9.750  -0.5937   0.06395   0.05675  -0.0599   1.0000   0.0476
  -9.500  -0.6260   0.06266   0.05546  -0.0536   1.0000   0.0474
  -9.250  -0.6552   0.06149   0.05422  -0.0474   1.0000   0.0473
  -9.000  -0.6653   0.05901   0.05153  -0.0451   0.9945   0.0477
  -8.750  -0.6562   0.05532   0.04742  -0.0462   0.9824   0.0490
  -8.500  -0.6467   0.05174   0.04334  -0.0464   0.9708   0.0503
  -8.250  -0.6326   0.04850   0.03960  -0.0464   0.9604   0.0511
  -8.000  -0.6159   0.04554   0.03608  -0.0460   0.9504   0.0522
  -7.750  -0.5892   0.04324   0.03361  -0.0472   0.9434   0.0547
  -7.500  -0.5664   0.04151   0.03168  -0.0474   0.9345   0.0577
  -7.250  -0.5328   0.03928   0.02896  -0.0489   0.9292   0.0615
  -7.000  -0.5069   0.03764   0.02726  -0.0490   0.9207   0.0643
  -6.750  -0.4717   0.03611   0.02555  -0.0506   0.9153   0.0706
  -6.500  -0.4412   0.03473   0.02413  -0.0514   0.9088   0.0769
  -6.250  -0.4105   0.03350   0.02275  -0.0521   0.9020   0.0860
  -6.000  -0.3757   0.03216   0.02140  -0.0538   0.8972   0.1000
  -5.750  -0.3576   0.03123   0.02049  -0.0525   0.8882   0.1151
  -5.500  -0.3317   0.03003   0.01938  -0.0528   0.8820   0.1428
  -5.250  -0.3172   0.02898   0.01855  -0.0512   0.8735   0.1774
  -5.000  -0.3010   0.02773   0.01771  -0.0500   0.8661   0.2395
  -4.750  -0.2913   0.02664   0.01725  -0.0474   0.8583   0.3360
  -4.500  -0.2798   0.02605   0.01726  -0.0442   0.8503   0.4535
  -4.250  -0.2559   0.02592   0.01737  -0.0424   0.8450   0.5530
  -4.000  -0.2456   0.02618   0.01767  -0.0385   0.8357   0.6068
  -3.750  -0.2169   0.02637   0.01780  -0.0374   0.8305   0.6598
  -3.500  -0.1972   0.02673   0.01808  -0.0349   0.8228   0.6975
  -3.250  -0.1677   0.02706   0.01830  -0.0340   0.8167   0.7329
  -3.000  -0.1253   0.02739   0.01845  -0.0351   0.8128   0.7657
  -2.750  -0.1026   0.02779   0.01872  -0.0335   0.8047   0.7911
  -2.500  -0.0612   0.02807   0.01880  -0.0352   0.7995   0.8122
  -2.250  -0.0132   0.02817   0.01866  -0.0383   0.7956   0.8292
  -2.000   0.0122   0.02849   0.01886  -0.0380   0.7874   0.8453
  -1.750   0.0621   0.02865   0.01881  -0.0419   0.7824   0.8565
  -1.500   0.1115   0.02861   0.01856  -0.0457   0.7784   0.8677
  -1.250   0.1373   0.02894   0.01880  -0.0459   0.7698   0.8814
  -1.000   0.1859   0.02900   0.01869  -0.0499   0.7646   0.8908
  -0.750   0.2311   0.02895   0.01849  -0.0532   0.7599   0.9010
  -0.500   0.2560   0.02933   0.01880  -0.0536   0.7510   0.9142
  -0.250   0.3042   0.02924   0.01859  -0.0575   0.7460   0.9228
   0.000   0.3362   0.02950   0.01878  -0.0591   0.7383   0.9344
   0.250   0.3714   0.02959   0.01881  -0.0611   0.7314   0.9458
   0.500   0.4189   0.02937   0.01847  -0.0649   0.7269   0.9542
   0.750   0.4456   0.02985   0.01896  -0.0661   0.7171   0.9671
   1.000   0.4889   0.02967   0.01871  -0.0693   0.7117   0.9764
   1.250   0.5215   0.02997   0.01902  -0.0715   0.7028   0.9882
   1.500   0.5644   0.02983   0.01884  -0.0749   0.6964   0.9974
   1.750   0.5772   0.03016   0.01917  -0.0733   0.6880   1.0000
   2.000   0.5860   0.03038   0.01936  -0.0706   0.6801   1.0000
   2.250   0.5900   0.03078   0.01974  -0.0672   0.6717   1.0000
   2.500   0.5976   0.03107   0.02000  -0.0642   0.6636   1.0000
   2.750   0.6017   0.03151   0.02042  -0.0606   0.6550   1.0000
   3.000   0.6113   0.03179   0.02068  -0.0578   0.6468   1.0000
   3.250   0.6144   0.03233   0.02120  -0.0541   0.6377   1.0000
   3.500   0.6297   0.03250   0.02133  -0.0520   0.6299   1.0000
   3.750   0.6304   0.03321   0.02202  -0.0480   0.6200   1.0000
   4.000   0.6526   0.03319   0.02200  -0.0468   0.6130   1.0000
   4.250   0.6506   0.03407   0.02286  -0.0425   0.6023   1.0000
   4.500   0.6799   0.03379   0.02258  -0.0421   0.5961   1.0000
   4.750   0.6753   0.03481   0.02360  -0.0375   0.5845   1.0000
   5.000   0.7116   0.03424   0.02305  -0.0379   0.5790   1.0000
   5.250   0.7046   0.03538   0.02419  -0.0331   0.5667   1.0000
   5.500   0.7197   0.03566   0.02449  -0.0310   0.5580   1.0000
   5.750   0.7377   0.03578   0.02463  -0.0292   0.5490   1.0000
   6.000   0.7349   0.03673   0.02559  -0.0249   0.5376   1.0000
   6.250   0.7741   0.03598   0.02488  -0.0255   0.5311   1.0000
   6.500   0.7636   0.03726   0.02617  -0.0204   0.5186   1.0000
   6.750   0.7741   0.03770   0.02666  -0.0178   0.5083   1.0000
   7.000   0.8018   0.03733   0.02633  -0.0170   0.5000   1.0000
   7.250   0.7989   0.03849   0.02752  -0.0133   0.4875   1.0000
   7.500   0.8168   0.03861   0.02767  -0.0115   0.4776   1.0000
   7.750   0.8412   0.03835   0.02748  -0.0103   0.4681   1.0000
   8.000   0.8417   0.03950   0.02867  -0.0073   0.4553   1.0000
   8.250   0.8550   0.03996   0.02917  -0.0054   0.4442   1.0000
   8.500   0.8891   0.03905   0.02830  -0.0049   0.4350   1.0000
   8.750   0.8883   0.04044   0.02976  -0.0021   0.4218   1.0000
   9.000   0.8950   0.04144   0.03081   0.0000   0.4093   1.0000
   9.250   0.9136   0.04160   0.03100   0.0014   0.3982   1.0000
   9.500   0.9400   0.04119   0.03062   0.0025   0.3873   1.0000
   9.750   0.9409   0.04271   0.03221   0.0047   0.3743   1.0000
  10.000   0.9478   0.04389   0.03343   0.0064   0.3620   1.0000
  10.250   0.9631   0.04440   0.03396   0.0078   0.3504   1.0000
  10.500   0.9874   0.04419   0.03373   0.0090   0.3391   1.0000
  10.750   0.9859   0.04614   0.03577   0.0108   0.3267   1.0000
  11.000   0.9899   0.04772   0.03740   0.0123   0.3150   1.0000
  11.250   1.0024   0.04856   0.03825   0.0136   0.3039   1.0000
  11.500   1.0193   0.04903   0.03870   0.0148   0.2929   1.0000
  11.750   1.0138   0.05162   0.04141   0.0161   0.2819   1.0000
  12.000   1.0213   0.05305   0.04287   0.0172   0.2717   1.0000
  12.250   1.0386   0.05353   0.04332   0.0183   0.2617   1.0000
  12.500   1.0286   0.05680   0.04675   0.0192   0.2521   1.0000
  12.750   1.0409   0.05787   0.04782   0.0202   0.2432   1.0000
  13.000   1.0386   0.06047   0.05052   0.0210   0.2342   1.0000
  13.250   1.0398   0.06279   0.05293   0.0216   0.2259   1.0000
  13.500   1.0456   0.06461   0.05479   0.0223   0.2177   1.0000
  13.750   1.0389   0.06802   0.05834   0.0226   0.2105   1.0000
  14.000   1.0420   0.07023   0.06061   0.0230   0.2029   1.0000
  14.250   1.0340   0.07396   0.06446   0.0229   0.1962   1.0000
  14.500   1.0241   0.07806   0.06868   0.0226   0.1895   1.0000
  14.750   1.0310   0.07996   0.07061   0.0229   0.1833   1.0000
  15.000   0.9790   0.09079   0.08169   0.0196   0.1777   1.0000
  15.250   1.0329   0.08543   0.07623   0.0228   0.1709   1.0000
  15.500   0.8910   0.11324   0.10429   0.0111   0.1642   1.0000
  15.750   0.9017   0.11458   0.10570   0.0113   0.1591   1.0000
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