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S1016 (s1016-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: S1016 (s1016-il)
Reynolds number: 50,000
Max Cl/Cd: 28.14 at α=6°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1016-il-50000.txt
Download as CSV file: xf-s1016-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1016                                           
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.8276   0.07577   0.06804  -0.0490   1.0000   0.2112
 -11.750  -0.8736   0.07209   0.06431  -0.0438   1.0000   0.2103
 -11.500  -0.9180   0.06909   0.06122  -0.0376   1.0000   0.2094
 -11.250  -0.9605   0.06668   0.05871  -0.0304   1.0000   0.2088
 -11.000  -1.0011   0.06453   0.05642  -0.0227   1.0000   0.2085
 -10.750  -1.0362   0.06202   0.05370  -0.0155   1.0000   0.2090
 -10.500  -1.0680   0.05949   0.05089  -0.0085   1.0000   0.2102
 -10.250  -1.0964   0.05699   0.04802  -0.0016   1.0000   0.2117
 -10.000  -1.0680   0.05538   0.04662  -0.0017   1.0000   0.2201
  -9.750  -1.0813   0.05313   0.04409   0.0035   1.0000   0.2242
  -9.500  -1.0992   0.05083   0.04135   0.0094   1.0000   0.2280
  -9.250  -1.0802   0.04921   0.03984   0.0105   1.0000   0.2365
  -9.000  -1.0839   0.04727   0.03759   0.0148   1.0000   0.2431
  -8.750  -1.0725   0.04553   0.03579   0.0169   1.0000   0.2514
  -8.500  -1.0684   0.04392   0.03394   0.0202   1.0000   0.2606
  -8.250  -1.0520   0.04244   0.03249   0.0218   1.0000   0.2712
  -8.000  -1.0449   0.04087   0.03068   0.0247   1.0000   0.2820
  -7.750  -1.0305   0.03960   0.02936   0.0267   1.0000   0.2952
  -7.500  -1.0126   0.03835   0.02817   0.0282   1.0000   0.3098
  -7.250  -0.9959   0.03715   0.02699   0.0298   1.0000   0.3260
  -7.000  -0.9789   0.03599   0.02585   0.0315   1.0000   0.3443
  -6.750  -0.9633   0.03488   0.02476   0.0334   1.0000   0.3654
  -6.500  -0.9411   0.03389   0.02398   0.0344   1.0000   0.3906
  -6.250  -0.9249   0.03290   0.02310   0.0364   1.0000   0.4199
  -6.000  -0.9024   0.03206   0.02260   0.0377   1.0000   0.4574
  -5.750  -0.8785   0.03148   0.02246   0.0392   1.0000   0.5057
  -5.500  -0.8353   0.03233   0.02395   0.0394   1.0000   0.5733
  -5.250  -0.7478   0.03742   0.02922   0.0361   1.0000   0.6347
  -5.000  -0.6741   0.04243   0.03399   0.0344   1.0000   0.6666
  -4.750  -0.6294   0.04539   0.03677   0.0350   1.0000   0.6961
  -4.500  -0.5586   0.04889   0.04000   0.0318   1.0000   0.7208
  -4.250  -0.5138   0.05073   0.04167   0.0309   1.0000   0.7475
  -4.000  -0.4839   0.05178   0.04258   0.0315   1.0000   0.7758
  -3.750  -0.4201   0.05303   0.04364   0.0269   1.0000   0.8007
  -3.500  -0.3815   0.05340   0.04387   0.0253   1.0000   0.8288
  -3.250  -0.3378   0.05356   0.04389   0.0225   1.0000   0.8575
  -3.000  -0.2792   0.05334   0.04353   0.0169   1.0000   0.8865
  -2.750  -0.2244   0.05285   0.04291   0.0111   1.0000   0.9177
  -2.500  -0.1632   0.05216   0.04208   0.0035   1.0000   0.9516
  -2.250  -0.0675   0.05091   0.04065  -0.0118   1.0000   0.9915
  -2.000  -0.0370   0.05012   0.03977  -0.0153   1.0000   1.0000
  -1.750  -0.0331   0.04962   0.03924  -0.0135   1.0000   1.0000
  -1.500  -0.0289   0.04920   0.03878  -0.0116   1.0000   1.0000
  -1.250  -0.0245   0.04884   0.03840  -0.0098   1.0000   1.0000
  -1.000  -0.0198   0.04856   0.03810  -0.0078   1.0000   1.0000
  -0.750  -0.0150   0.04834   0.03786  -0.0059   1.0000   1.0000
  -0.500  -0.0101   0.04818   0.03770  -0.0039   1.0000   1.0000
  -0.250  -0.0051   0.04809   0.03759  -0.0020   1.0000   1.0000
   0.000   0.0000   0.04806   0.03756   0.0000   1.0000   1.0000
   0.250   0.0051   0.04808   0.03759   0.0020   1.0000   1.0000
   0.500   0.0101   0.04818   0.03769   0.0039   1.0000   1.0000
   0.750   0.0150   0.04833   0.03785   0.0059   1.0000   1.0000
   1.000   0.0198   0.04855   0.03809   0.0078   1.0000   1.0000
   1.250   0.0245   0.04883   0.03839   0.0098   1.0000   1.0000
   1.500   0.0289   0.04918   0.03876   0.0116   1.0000   1.0000
   1.750   0.0331   0.04960   0.03921   0.0135   1.0000   1.0000
   2.000   0.0370   0.05009   0.03975   0.0153   1.0000   1.0000
   2.250   0.0678   0.05087   0.04061   0.0117   0.9914   1.0000
   2.500   0.1633   0.05213   0.04205  -0.0035   0.9515   1.0000
   2.750   0.2243   0.05282   0.04288  -0.0111   0.9179   1.0000
   3.000   0.2792   0.05332   0.04350  -0.0169   0.8867   1.0000
   3.250   0.3387   0.05354   0.04387  -0.0227   0.8578   1.0000
   3.500   0.3810   0.05338   0.04384  -0.0253   0.8289   1.0000
   3.750   0.4202   0.05300   0.04360  -0.0270   0.8009   1.0000
   4.000   0.4834   0.05176   0.04256  -0.0315   0.7758   1.0000
   4.250   0.5132   0.05074   0.04168  -0.0309   0.7477   1.0000
   4.500   0.5588   0.04887   0.03998  -0.0318   0.7210   1.0000
   4.750   0.6286   0.04542   0.03679  -0.0349   0.6962   1.0000
   5.000   0.6734   0.04245   0.03402  -0.0343   0.6667   1.0000
   5.250   0.7473   0.03744   0.02923  -0.0361   0.6349   1.0000
   5.500   0.8352   0.03232   0.02395  -0.0394   0.5736   1.0000
   5.750   0.8785   0.03146   0.02245  -0.0392   0.5058   1.0000
   6.000   0.9022   0.03206   0.02260  -0.0377   0.4575   1.0000
   6.250   0.9250   0.03288   0.02308  -0.0364   0.4201   1.0000
   6.500   0.9410   0.03388   0.02397  -0.0344   0.3907   1.0000
   6.750   0.9631   0.03487   0.02475  -0.0334   0.3654   1.0000
   7.000   0.9788   0.03597   0.02584  -0.0315   0.3443   1.0000
   7.250   0.9959   0.03714   0.02699  -0.0298   0.3260   1.0000
   7.500   1.0123   0.03834   0.02816  -0.0281   0.3097   1.0000
   7.750   1.0305   0.03959   0.02935  -0.0267   0.2952   1.0000
   8.000   1.0448   0.04086   0.03067  -0.0247   0.2821   1.0000
   8.250   1.0519   0.04243   0.03247  -0.0218   0.2711   1.0000
   8.500   1.0683   0.04392   0.03394  -0.0202   0.2606   1.0000
   8.750   1.0724   0.04552   0.03578  -0.0169   0.2514   1.0000
   9.000   1.0835   0.04725   0.03757  -0.0147   0.2430   1.0000
   9.250   1.0802   0.04919   0.03981  -0.0105   0.2364   1.0000
   9.500   1.0991   0.05080   0.04132  -0.0094   0.2280   1.0000
   9.750   1.0812   0.05313   0.04408  -0.0034   0.2242   1.0000
  10.000   1.0679   0.05538   0.04662   0.0017   0.2203   1.0000
  10.250   1.0968   0.05698   0.04801   0.0015   0.2118   1.0000
  10.500   1.0674   0.05948   0.05087   0.0085   0.2102   1.0000
  10.750   1.0365   0.06200   0.05367   0.0155   0.2090   1.0000
  11.000   1.0013   0.06452   0.05641   0.0226   0.2085   1.0000
  11.250   0.9605   0.06667   0.05870   0.0304   0.2088   1.0000
  11.500   0.9177   0.06908   0.06121   0.0376   0.2094   1.0000
  11.750   0.8726   0.07208   0.06430   0.0439   0.2103   1.0000
  12.000   0.8276   0.07572   0.06798   0.0491   0.2112   1.0000
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