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S3010-103-84 (s3010-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S3010-103-84 (s3010-il)
Reynolds number: 50,000
Max Cl/Cd: 36.25 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s3010-il-50000-n5.txt
Download as CSV file: xf-s3010-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S3010-103-84                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.4323   0.10367   0.09663  -0.0222   1.0000   0.0522
  -9.250  -0.4233   0.10023   0.09322  -0.0223   1.0000   0.0515
  -9.000  -0.4191   0.09643   0.08947  -0.0237   1.0000   0.0511
  -8.750  -0.4166   0.09251   0.08562  -0.0255   1.0000   0.0507
  -8.500  -0.4159   0.08844   0.08163  -0.0277   1.0000   0.0505
  -8.250  -0.4165   0.08429   0.07756  -0.0300   1.0000   0.0502
  -8.000  -0.4184   0.08014   0.07350  -0.0325   1.0000   0.0498
  -7.750  -0.4213   0.07529   0.06874  -0.0364   1.0000   0.0495
  -7.500  -0.4224   0.07020   0.06368  -0.0403   1.0000   0.0489
  -7.250  -0.4249   0.06506   0.05850  -0.0436   1.0000   0.0486
  -7.000  -0.4266   0.06027   0.05363  -0.0460   1.0000   0.0483
  -6.750  -0.4271   0.05582   0.04904  -0.0474   1.0000   0.0480
  -6.500  -0.4262   0.05171   0.04471  -0.0479   1.0000   0.0479
  -6.250  -0.4227   0.04799   0.04072  -0.0477   1.0000   0.0478
  -6.000  -0.4167   0.04457   0.03698  -0.0470   1.0000   0.0477
  -5.750  -0.4082   0.04138   0.03341  -0.0462   1.0000   0.0478
  -5.500  -0.3970   0.03848   0.03010  -0.0452   1.0000   0.0482
  -5.250  -0.3834   0.03593   0.02713  -0.0442   1.0000   0.0487
  -5.000  -0.3676   0.03366   0.02444  -0.0431   1.0000   0.0496
  -4.750  -0.3502   0.03167   0.02202  -0.0420   1.0000   0.0510
  -4.500  -0.3164   0.02976   0.01986  -0.0440   0.9924   0.0544
  -4.250  -0.2780   0.02818   0.01802  -0.0464   0.9833   0.0598
  -4.000  -0.2404   0.02655   0.01609  -0.0482   0.9739   0.0645
  -3.750  -0.2037   0.02532   0.01477  -0.0501   0.9640   0.0738
  -3.500  -0.1652   0.02412   0.01354  -0.0523   0.9547   0.0918
  -3.250  -0.1261   0.02291   0.01249  -0.0549   0.9452   0.1359
  -3.000  -0.0901   0.02175   0.01175  -0.0571   0.9345   0.2214
  -2.750  -0.0539   0.02081   0.01126  -0.0591   0.9244   0.3320
  -2.500  -0.0201   0.02009   0.01103  -0.0601   0.9140   0.4555
  -2.250   0.0068   0.01960   0.01094  -0.0592   0.9016   0.5716
  -2.000   0.0319   0.01924   0.01090  -0.0574   0.8895   0.6839
  -1.750   0.0605   0.01896   0.01077  -0.0556   0.8785   0.7971
  -1.500   0.1156   0.01865   0.01037  -0.0592   0.8696   0.9217
  -1.250   0.1745   0.01846   0.00983  -0.0651   0.8582   1.0000
  -1.000   0.2007   0.01854   0.00963  -0.0649   0.8438   1.0000
  -0.750   0.2270   0.01864   0.00947  -0.0646   0.8298   1.0000
  -0.500   0.2532   0.01875   0.00934  -0.0642   0.8162   1.0000
  -0.250   0.2797   0.01886   0.00923  -0.0637   0.8029   1.0000
   0.000   0.3061   0.01896   0.00914  -0.0631   0.7898   1.0000
   0.250   0.3308   0.01912   0.00913  -0.0624   0.7755   1.0000
   0.500   0.3557   0.01928   0.00914  -0.0616   0.7613   1.0000
   0.750   0.3808   0.01944   0.00917  -0.0608   0.7473   1.0000
   1.000   0.4063   0.01961   0.00921  -0.0601   0.7333   1.0000
   1.250   0.4318   0.01978   0.00927  -0.0594   0.7194   1.0000
   1.500   0.4574   0.01995   0.00933  -0.0586   0.7055   1.0000
   1.750   0.4831   0.02013   0.00941  -0.0579   0.6917   1.0000
   2.000   0.5089   0.02030   0.00950  -0.0571   0.6779   1.0000
   2.250   0.5347   0.02048   0.00959  -0.0564   0.6641   1.0000
   2.500   0.5605   0.02065   0.00971  -0.0556   0.6503   1.0000
   2.750   0.5859   0.02087   0.00988  -0.0548   0.6359   1.0000
   3.000   0.6112   0.02111   0.01007  -0.0541   0.6211   1.0000
   3.250   0.6364   0.02136   0.01031  -0.0533   0.6062   1.0000
   3.500   0.6615   0.02162   0.01054  -0.0526   0.5913   1.0000
   3.750   0.6866   0.02190   0.01078  -0.0518   0.5761   1.0000
   4.000   0.7117   0.02218   0.01106  -0.0511   0.5609   1.0000
   4.250   0.7366   0.02248   0.01137  -0.0503   0.5456   1.0000
   4.500   0.7614   0.02280   0.01168  -0.0495   0.5301   1.0000
   4.750   0.7861   0.02313   0.01202  -0.0487   0.5146   1.0000
   5.000   0.8106   0.02349   0.01240  -0.0480   0.4989   1.0000
   5.250   0.8349   0.02387   0.01279  -0.0472   0.4831   1.0000
   5.500   0.8589   0.02427   0.01320  -0.0464   0.4670   1.0000
   5.750   0.8823   0.02474   0.01372  -0.0456   0.4502   1.0000
   6.000   0.9053   0.02523   0.01429  -0.0448   0.4334   1.0000
   6.250   0.9282   0.02574   0.01485  -0.0439   0.4165   1.0000
   6.500   0.9507   0.02628   0.01543  -0.0431   0.3996   1.0000
   6.750   0.9728   0.02684   0.01607  -0.0422   0.3828   1.0000
   7.000   0.9946   0.02744   0.01671  -0.0412   0.3661   1.0000
   7.250   1.0160   0.02807   0.01739  -0.0403   0.3496   1.0000
   7.500   1.0369   0.02874   0.01810  -0.0393   0.3333   1.0000
   7.750   1.0572   0.02946   0.01889  -0.0383   0.3173   1.0000
   8.000   1.0767   0.03025   0.01972  -0.0373   0.3014   1.0000
   8.250   1.0952   0.03113   0.02069  -0.0362   0.2855   1.0000
   8.500   1.1130   0.03207   0.02170  -0.0351   0.2702   1.0000
   8.750   1.1301   0.03306   0.02279  -0.0340   0.2553   1.0000
   9.000   1.1466   0.03411   0.02390  -0.0328   0.2414   1.0000
   9.250   1.1620   0.03522   0.02506  -0.0316   0.2279   1.0000
   9.500   1.1761   0.03647   0.02643  -0.0303   0.2150   1.0000
   9.750   1.1884   0.03782   0.02793  -0.0290   0.2026   1.0000
  10.000   1.1998   0.03927   0.02953  -0.0276   0.1911   1.0000
  10.250   1.2109   0.04074   0.03108  -0.0263   0.1809   1.0000
  10.500   1.2217   0.04212   0.03245  -0.0249   0.1713   1.0000
  10.750   1.2258   0.04402   0.03462  -0.0232   0.1622   1.0000
  11.000   1.2324   0.04573   0.03638  -0.0217   0.1544   1.0000
  11.250   1.2352   0.04773   0.03855  -0.0202   0.1468   1.0000
  11.500   1.2388   0.04987   0.04080  -0.0190   0.1401   1.0000
  11.750   1.2394   0.05229   0.04343  -0.0180   0.1338   1.0000
  12.000   1.2429   0.05456   0.04577  -0.0172   0.1280   1.0000
  12.250   1.2365   0.05793   0.04942  -0.0169   0.1229   1.0000
  12.500   1.2422   0.06006   0.05156  -0.0163   0.1176   1.0000
  12.750   1.2329   0.06416   0.05592  -0.0166   0.1139   1.0000
  13.000   1.2191   0.06896   0.06100  -0.0177   0.1105   1.0000
  13.250   1.2136   0.07277   0.06493  -0.0185   0.1066   1.0000
  13.500   1.2136   0.07605   0.06826  -0.0189   0.1028   1.0000
  13.750   1.1858   0.08376   0.07627  -0.0224   0.1016   1.0000
  14.000   1.1503   0.09356   0.08633  -0.0276   0.1010   1.0000
  14.250   1.0979   0.10810   0.10104  -0.0362   0.1015   1.0000
  14.500   1.0197   0.13183   0.12469  -0.0505   0.1018   1.0000
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