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S9037 (9%) (s9037-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S9037 (9%) (s9037-il)
Reynolds number: 50,000
Max Cl/Cd: 39.83 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s9037-il-50000-n5.txt
Download as CSV file: xf-s9037-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9037 (9%)                                      
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.2712   0.09842   0.09215  -0.0326   1.0000   0.1073
  -8.500  -0.2689   0.09516   0.08894  -0.0325   1.0000   0.1085
  -8.250  -0.2693   0.09206   0.08592  -0.0325   1.0000   0.1090
  -8.000  -0.2718   0.08905   0.08300  -0.0325   1.0000   0.1090
  -7.750  -0.2811   0.08317   0.07711  -0.0351   1.0000   0.0608
  -7.250  -0.3629   0.08767   0.08143  -0.0352   1.0000   0.0650
  -7.000  -0.3695   0.08277   0.07655  -0.0400   1.0000   0.0499
  -6.750  -0.3681   0.08005   0.07391  -0.0377   1.0000   0.0489
  -6.500  -0.3692   0.07723   0.07116  -0.0368   1.0000   0.0477
  -6.250  -0.3710   0.07423   0.06821  -0.0367   1.0000   0.0466
  -6.000  -0.3721   0.07091   0.06492  -0.0371   1.0000   0.0454
  -5.750  -0.3712   0.06736   0.06136  -0.0378   1.0000   0.0440
  -5.500  -0.3679   0.06329   0.05722  -0.0393   1.0000   0.0425
  -5.250  -0.3607   0.05835   0.05210  -0.0416   1.0000   0.0406
  -5.000  -0.3457   0.05256   0.04569  -0.0449   1.0000   0.0382
  -4.750  -0.3334   0.04908   0.04200  -0.0452   1.0000   0.0380
  -4.500  -0.3181   0.04559   0.03822  -0.0457   1.0000   0.0378
  -4.250  -0.2914   0.04178   0.03396  -0.0480   0.9968   0.0376
  -4.000  -0.2549   0.03782   0.02930  -0.0514   0.9907   0.0378
  -3.750  -0.2186   0.03444   0.02539  -0.0543   0.9847   0.0392
  -3.500  -0.1845   0.03244   0.02312  -0.0566   0.9778   0.0434
  -3.250  -0.1462   0.03019   0.02026  -0.0587   0.9718   0.0478
  -3.000  -0.1110   0.02822   0.01782  -0.0598   0.9651   0.0511
  -2.750  -0.0746   0.02689   0.01625  -0.0616   0.9584   0.0611
  -2.500  -0.0407   0.02562   0.01481  -0.0626   0.9509   0.0735
  -2.250  -0.0030   0.02446   0.01356  -0.0643   0.9441   0.1008
  -2.000   0.0314   0.02332   0.01260  -0.0658   0.9359   0.1604
  -1.750   0.0684   0.02188   0.01205  -0.0682   0.9293   0.3397
  -1.500   0.0894   0.02048   0.01199  -0.0662   0.9203   0.6477
  -1.250   0.1443   0.01991   0.01145  -0.0700   0.9144   1.0000
  -1.000   0.1772   0.02007   0.01118  -0.0711   0.9033   1.0000
  -0.750   0.2120   0.02023   0.01095  -0.0726   0.8930   1.0000
  -0.500   0.2515   0.02035   0.01074  -0.0747   0.8845   1.0000
  -0.250   0.2831   0.02049   0.01063  -0.0754   0.8732   1.0000
   0.000   0.3136   0.02064   0.01054  -0.0758   0.8616   1.0000
   0.250   0.3449   0.02076   0.01048  -0.0764   0.8502   1.0000
   0.500   0.3777   0.02085   0.01040  -0.0771   0.8394   1.0000
   0.750   0.4116   0.02089   0.01028  -0.0778   0.8291   1.0000
   1.000   0.4399   0.02101   0.01030  -0.0777   0.8164   1.0000
   1.250   0.4684   0.02113   0.01032  -0.0775   0.8036   1.0000
   1.500   0.4970   0.02123   0.01034  -0.0774   0.7909   1.0000
   1.750   0.5255   0.02132   0.01037  -0.0771   0.7780   1.0000
   2.000   0.5539   0.02140   0.01040  -0.0768   0.7649   1.0000
   2.250   0.5822   0.02147   0.01043  -0.0764   0.7514   1.0000
   2.500   0.6100   0.02154   0.01049  -0.0759   0.7375   1.0000
   2.750   0.6376   0.02161   0.01054  -0.0754   0.7231   1.0000
   3.000   0.6647   0.02169   0.01062  -0.0748   0.7082   1.0000
   3.250   0.6917   0.02178   0.01071  -0.0741   0.6929   1.0000
   3.500   0.7185   0.02188   0.01085  -0.0734   0.6772   1.0000
   3.750   0.7453   0.02198   0.01095  -0.0726   0.6613   1.0000
   4.000   0.7723   0.02208   0.01106  -0.0719   0.6450   1.0000
   4.250   0.7967   0.02230   0.01131  -0.0709   0.6267   1.0000
   4.500   0.8214   0.02251   0.01161  -0.0699   0.6079   1.0000
   4.750   0.8470   0.02268   0.01180  -0.0690   0.5894   1.0000
   5.000   0.8709   0.02296   0.01211  -0.0679   0.5695   1.0000
   5.250   0.8948   0.02325   0.01244  -0.0669   0.5493   1.0000
   5.500   0.9192   0.02354   0.01279  -0.0659   0.5294   1.0000
   5.750   0.9416   0.02395   0.01327  -0.0647   0.5078   1.0000
   6.000   0.9648   0.02432   0.01366  -0.0636   0.4868   1.0000
   6.250   0.9861   0.02481   0.01421  -0.0623   0.4642   1.0000
   6.500   1.0076   0.02530   0.01478  -0.0611   0.4420   1.0000
   6.750   1.0284   0.02586   0.01539  -0.0598   0.4197   1.0000
   7.000   1.0484   0.02650   0.01609  -0.0585   0.3972   1.0000
   7.250   1.0682   0.02715   0.01677  -0.0571   0.3753   1.0000
   7.500   1.0864   0.02793   0.01764  -0.0557   0.3526   1.0000
   7.750   1.1045   0.02871   0.01848  -0.0542   0.3311   1.0000
   8.000   1.1207   0.02960   0.01947  -0.0526   0.3084   1.0000
   8.250   1.1365   0.03054   0.02045  -0.0510   0.2873   1.0000
   8.500   1.1508   0.03157   0.02155  -0.0493   0.2661   1.0000
   8.750   1.1648   0.03266   0.02265  -0.0476   0.2471   1.0000
   9.000   1.1772   0.03388   0.02400  -0.0458   0.2277   1.0000
   9.250   1.1890   0.03516   0.02541  -0.0440   0.2103   1.0000
   9.500   1.1990   0.03652   0.02681  -0.0421   0.1939   1.0000
   9.750   1.2080   0.03798   0.02831  -0.0401   0.1791   1.0000
  10.000   1.2146   0.03951   0.02991  -0.0380   0.1652   1.0000
  10.250   1.2196   0.04119   0.03168  -0.0359   0.1520   1.0000
  10.500   1.2245   0.04303   0.03367  -0.0339   0.1399   1.0000
  10.750   1.2277   0.04502   0.03581  -0.0321   0.1287   1.0000
  11.000   1.2320   0.04718   0.03811  -0.0305   0.1191   1.0000
  11.250   1.2356   0.04935   0.04030  -0.0290   0.1109   1.0000
  11.500   1.2357   0.05191   0.04316  -0.0277   0.1024   1.0000
  11.750   1.2360   0.05460   0.04600  -0.0266   0.0953   1.0000
  12.000   1.2373   0.05742   0.04900  -0.0257   0.0891   1.0000
  12.250   1.2365   0.06054   0.05228  -0.0250   0.0836   1.0000
  12.500   1.2308   0.06413   0.05613  -0.0247   0.0785   1.0000
  12.750   1.2303   0.06705   0.05899  -0.0244   0.0738   1.0000
  13.000   1.2202   0.07188   0.06425  -0.0249   0.0707   1.0000
  13.250   1.2095   0.07677   0.06943  -0.0259   0.0679   1.0000
  13.500   1.2008   0.08130   0.07410  -0.0271   0.0649   1.0000
  13.750   1.1961   0.08532   0.07812  -0.0280   0.0615   1.0000
  14.000   1.1775   0.09217   0.08528  -0.0310   0.0607   1.0000
  14.250   1.1567   0.09983   0.09320  -0.0348   0.0602   1.0000
  14.500   1.1345   0.10843   0.10202  -0.0394   0.0603   1.0000
  14.750   1.1102   0.11818   0.11194  -0.0451   0.0608   1.0000
  15.000   1.0854   0.12899   0.12285  -0.0515   0.0615   1.0000
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