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SA7036 (sa7036-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SA7036 (sa7036-il)
Reynolds number: 200,000
Max Cl/Cd: 73 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sa7036-il-200000.txt
Download as CSV file: xf-sa7036-il-200000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SA7036                                          
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3915   0.09435   0.09091  -0.0360   1.0000   0.0401
  -8.500  -0.3942   0.09088   0.08751  -0.0386   1.0000   0.0402
  -8.250  -0.3984   0.08748   0.08417  -0.0402   1.0000   0.0403
  -8.000  -0.3894   0.08307   0.07978  -0.0348   1.0000   0.0427
  -7.750  -0.3925   0.08040   0.07717  -0.0346   1.0000   0.0432
  -7.500  -0.3963   0.07841   0.07524  -0.0331   1.0000   0.0447
  -7.250  -0.4072   0.07608   0.07300  -0.0322   1.0000   0.0458
  -7.000  -0.4168   0.07340   0.07037  -0.0326   1.0000   0.0479
  -6.750  -0.4260   0.07019   0.06719  -0.0334   1.0000   0.0483
  -6.500  -0.4333   0.06623   0.06321  -0.0358   1.0000   0.0502
  -6.250  -0.4382   0.06170   0.05835  -0.0405   1.0000   0.0522
  -6.000  -0.4398   0.05801   0.05438  -0.0409   1.0000   0.0528
  -5.750  -0.4379   0.05312   0.04975  -0.0392   1.0000   0.0546
  -5.500  -0.4233   0.05067   0.04732  -0.0393   0.9987   0.0566
  -5.000  -0.3041   0.02569   0.02201  -0.0555   0.9773   0.0720
  -4.750  -0.2718   0.02112   0.01700  -0.0597   0.9726   0.0824
  -4.500  -0.2804   0.02794   0.02247  -0.0563   0.9799   0.0440
  -4.250  -0.2428   0.02235   0.01577  -0.0568   0.9760   0.0312
  -4.000  -0.2038   0.02022   0.01331  -0.0589   0.9724   0.0323
  -3.750  -0.1665   0.01903   0.01195  -0.0608   0.9677   0.0355
  -3.500  -0.1306   0.01751   0.01023  -0.0620   0.9622   0.0364
  -3.250  -0.0899   0.01629   0.00889  -0.0642   0.9585   0.0389
  -3.000  -0.0545   0.01515   0.00775  -0.0657   0.9527   0.0456
  -2.750  -0.0163   0.01421   0.00679  -0.0676   0.9468   0.0573
  -2.500   0.0249   0.01246   0.00594  -0.0708   0.9435   0.2497
  -2.250   0.0554   0.01162   0.00577  -0.0717   0.9354   0.4317
  -2.000   0.0879   0.01074   0.00573  -0.0722   0.9303   0.6574
  -1.750   0.1134   0.01035   0.00566  -0.0708   0.9217   0.7689
  -1.500   0.1443   0.01001   0.00551  -0.0699   0.9159   0.8698
  -1.250   0.1954   0.00978   0.00524  -0.0736   0.9117   0.9567
  -1.000   0.2618   0.00951   0.00482  -0.0811   0.9077   0.9996
  -0.750   0.2889   0.00935   0.00453  -0.0807   0.8969   1.0000
  -0.500   0.3146   0.00920   0.00424  -0.0799   0.8859   1.0000
  -0.250   0.3374   0.00911   0.00405  -0.0786   0.8726   1.0000
   0.000   0.3610   0.00904   0.00387  -0.0773   0.8592   1.0000
   0.250   0.3851   0.00897   0.00370  -0.0762   0.8453   1.0000
   0.500   0.4097   0.00893   0.00355  -0.0751   0.8310   1.0000
   0.750   0.4347   0.00890   0.00342  -0.0742   0.8161   1.0000
   1.000   0.4600   0.00889   0.00332  -0.0733   0.8004   1.0000
   1.250   0.4850   0.00892   0.00327  -0.0724   0.7825   1.0000
   1.500   0.5105   0.00896   0.00321  -0.0716   0.7642   1.0000
   1.750   0.5362   0.00903   0.00317  -0.0709   0.7461   1.0000
   2.000   0.5618   0.00913   0.00318  -0.0701   0.7267   1.0000
   2.250   0.5873   0.00924   0.00321  -0.0694   0.7066   1.0000
   2.500   0.6130   0.00939   0.00324  -0.0688   0.6867   1.0000
   2.750   0.6383   0.00955   0.00332  -0.0681   0.6646   1.0000
   3.000   0.6637   0.00974   0.00342  -0.0674   0.6432   1.0000
   3.250   0.6889   0.00993   0.00353  -0.0668   0.6205   1.0000
   3.500   0.7141   0.01015   0.00366  -0.0661   0.5986   1.0000
   3.750   0.7392   0.01038   0.00381  -0.0655   0.5761   1.0000
   4.000   0.7641   0.01063   0.00401  -0.0649   0.5534   1.0000
   4.250   0.7889   0.01091   0.00420  -0.0642   0.5310   1.0000
   4.500   0.8136   0.01118   0.00442  -0.0636   0.5074   1.0000
   4.750   0.8380   0.01148   0.00465  -0.0629   0.4838   1.0000
   5.000   0.8620   0.01182   0.00492  -0.0622   0.4599   1.0000
   5.250   0.8861   0.01214   0.00521  -0.0616   0.4353   1.0000
   5.500   0.9100   0.01250   0.00551  -0.0609   0.4117   1.0000
   5.750   0.9333   0.01291   0.00584  -0.0601   0.3885   1.0000
   6.000   0.9569   0.01329   0.00623  -0.0594   0.3645   1.0000
   6.250   0.9800   0.01372   0.00662  -0.0587   0.3413   1.0000
   6.500   1.0024   0.01420   0.00702  -0.0579   0.3176   1.0000
   6.750   1.0250   0.01466   0.00747  -0.0571   0.2933   1.0000
   7.000   1.0470   0.01518   0.00795  -0.0563   0.2697   1.0000
   7.250   1.0682   0.01576   0.00848  -0.0553   0.2471   1.0000
   7.500   1.0898   0.01630   0.00903  -0.0545   0.2237   1.0000
   7.750   1.1104   0.01693   0.00962  -0.0535   0.2013   1.0000
   8.000   1.1303   0.01762   0.01026  -0.0525   0.1793   1.0000
   8.250   1.1500   0.01832   0.01096  -0.0514   0.1575   1.0000
   8.500   1.1676   0.01920   0.01177  -0.0501   0.1374   1.0000
   8.750   1.1859   0.02003   0.01262  -0.0489   0.1167   1.0000
   9.000   1.2009   0.02111   0.01361  -0.0473   0.0987   1.0000
   9.250   1.2150   0.02228   0.01476  -0.0455   0.0830   1.0000
   9.500   1.2278   0.02352   0.01601  -0.0436   0.0703   1.0000
   9.750   1.2370   0.02502   0.01748  -0.0413   0.0607   1.0000
  10.000   1.2506   0.02593   0.01853  -0.0394   0.0523   1.0000
  10.250   1.2573   0.02736   0.02001  -0.0368   0.0459   1.0000
  10.500   1.2631   0.02872   0.02141  -0.0343   0.0397   1.0000
  10.750   1.2698   0.03024   0.02310  -0.0320   0.0347   1.0000
  11.000   1.2731   0.03195   0.02485  -0.0297   0.0305   1.0000
  11.250   1.2737   0.03430   0.02735  -0.0272   0.0269   1.0000
  11.500   1.2783   0.03601   0.02919  -0.0254   0.0239   1.0000
  11.750   1.2773   0.03837   0.03157  -0.0237   0.0215   1.0000
  12.000   1.2770   0.04142   0.03481  -0.0219   0.0200   1.0000
  12.250   1.2794   0.04392   0.03752  -0.0206   0.0188   1.0000
  12.500   1.2803   0.04672   0.04052  -0.0195   0.0179   1.0000
  12.750   1.2795   0.04973   0.04373  -0.0186   0.0172   1.0000
  13.000   1.2770   0.05295   0.04713  -0.0181   0.0165   1.0000
  13.250   1.2733   0.05647   0.05084  -0.0180   0.0162   1.0000
  13.500   1.2674   0.06037   0.05492  -0.0183   0.0158   1.0000
  13.750   1.2593   0.06472   0.05945  -0.0189   0.0155   1.0000
  14.000   1.2497   0.06948   0.06443  -0.0201   0.0154   1.0000
  14.250   1.2373   0.07487   0.07004  -0.0219   0.0153   1.0000
  14.500   1.2231   0.08079   0.07617  -0.0244   0.0152   1.0000
  14.750   1.2074   0.08726   0.08288  -0.0276   0.0153   1.0000
  15.000   1.1905   0.09435   0.09019  -0.0316   0.0154   1.0000
  15.250   1.1707   0.10257   0.09864  -0.0365   0.0155   1.0000
  15.500   1.1455   0.11267   0.10902  -0.0430   0.0159   1.0000
  15.750   1.1169   0.12445   0.12105  -0.0508   0.0164   1.0000
  16.000   1.0733   0.14177   0.13862  -0.0624   0.0176   1.0000
  16.250   1.0286   0.16161   0.15856  -0.0746   0.0193   1.0000
  16.500   1.0047   0.17594   0.17284  -0.0822   0.0203   1.0000
  16.750   0.9960   0.18538   0.18226  -0.0868   0.0207   1.0000
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