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Ornithopter airfoil. (s1020-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: Ornithopter airfoil. (s1020-il)
Reynolds number: 100,000
Max Cl/Cd: 49.76 at α=10.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1020-il-100000.txt
Download as CSV file: xf-s1020-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: Ornithopter airfoil.                            
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.000  -0.3153   0.10803   0.10387  -0.0522   0.9690   0.1287
  -7.750  -0.3079   0.10489   0.10073  -0.0556   0.9635   0.1358
  -7.500  -0.3584   0.10254   0.09852  -0.0620   0.9515   0.1388
  -7.250  -0.3006   0.09808   0.09396  -0.0598   0.9512   0.1443
  -7.000  -0.3045   0.09571   0.09162  -0.0601   0.9432   0.1496
  -6.500  -0.3171   0.08938   0.08538  -0.0631   0.9278   0.1590
  -5.750  -0.3339   0.05307   0.04736  -0.0977   0.9041   0.0782
  -5.500  -0.3057   0.04696   0.04018  -0.1009   0.8991   0.0669
  -5.250  -0.2690   0.04317   0.03595  -0.1041   0.8957   0.0647
  -5.000  -0.2422   0.04074   0.03306  -0.1049   0.8902   0.0634
  -4.750  -0.2140   0.03878   0.03070  -0.1056   0.8845   0.0630
  -4.500  -0.1741   0.03700   0.02853  -0.1078   0.8809   0.0643
  -4.250  -0.1488   0.03618   0.02742  -0.1076   0.8746   0.0669
  -4.000  -0.1201   0.03486   0.02602  -0.1080   0.8690   0.0702
  -3.750  -0.0807   0.03370   0.02489  -0.1100   0.8655   0.0749
  -3.500  -0.0606   0.03326   0.02436  -0.1089   0.8583   0.0804
  -3.250  -0.0290   0.03233   0.02352  -0.1098   0.8530   0.0941
  -3.000   0.0143   0.02955   0.02224  -0.1141   0.8504   0.3269
  -2.750   0.0310   0.02985   0.02287  -0.1125   0.8424   0.4478
  -2.500   0.0598   0.03031   0.02346  -0.1122   0.8369   0.5305
  -2.250   0.0981   0.03052   0.02364  -0.1130   0.8337   0.5796
  -2.000   0.1039   0.03118   0.02430  -0.1095   0.8236   0.6029
  -1.750   0.1392   0.03124   0.02431  -0.1100   0.8198   0.6353
  -1.500   0.1497   0.03182   0.02488  -0.1073   0.8108   0.6562
  -1.250   0.1807   0.03186   0.02486  -0.1073   0.8059   0.6825
  -1.000   0.2192   0.03167   0.02460  -0.1083   0.8032   0.7082
  -0.750   0.2214   0.03245   0.02538  -0.1047   0.7924   0.7253
  -0.500   0.2570   0.03220   0.02509  -0.1053   0.7890   0.7480
  -0.250   0.2628   0.03291   0.02581  -0.1022   0.7793   0.7661
   0.000   0.2942   0.03276   0.02560  -0.1024   0.7750   0.7893
   0.250   0.3317   0.03231   0.02511  -0.1031   0.7725   0.8128
   0.500   0.3296   0.03327   0.02610  -0.0991   0.7610   0.8345
   0.750   0.3630   0.03279   0.02561  -0.0991   0.7581   0.8644
   1.000   0.3608   0.03362   0.02652  -0.0949   0.7474   0.9004
   1.250   0.4130   0.03307   0.02597  -0.0993   0.7439   1.0000
   1.500   0.4708   0.03271   0.02542  -0.1053   0.7420   1.0000
   1.750   0.4802   0.03424   0.02684  -0.1049   0.7302   1.0000
   2.000   0.5292   0.03388   0.02633  -0.1086   0.7277   1.0000
   2.250   0.5356   0.03544   0.02781  -0.1071   0.7166   1.0000
   2.500   0.5785   0.03516   0.02743  -0.1094   0.7134   1.0000
   2.750   0.6257   0.03458   0.02676  -0.1121   0.7115   1.0000
   3.000   0.6243   0.03650   0.02864  -0.1093   0.6992   1.0000
   3.250   0.6692   0.03593   0.02801  -0.1115   0.6970   1.0000
   3.500   0.7171   0.03510   0.02713  -0.1139   0.6955   1.0000
   3.750   0.7112   0.03734   0.02937  -0.1107   0.6824   1.0000
   4.000   0.7116   0.03930   0.03132  -0.1082   0.6708   1.0000
   4.250   0.7531   0.03873   0.03072  -0.1097   0.6679   1.0000
   4.500   0.7820   0.03895   0.03095  -0.1099   0.6627   1.0000
   4.750   0.8512   0.03640   0.02839  -0.1140   0.6653   1.0000
   5.000   0.8022   0.04177   0.03378  -0.1069   0.6438   1.0000
   5.250   0.8347   0.04163   0.03365  -0.1074   0.6387   1.0000
   5.500   0.8804   0.04047   0.03254  -0.1089   0.6367   1.0000
   5.750   0.9322   0.03879   0.03089  -0.1109   0.6358   1.0000
   6.000   0.9889   0.03696   0.02913  -0.1137   0.6351   1.0000
   6.250   0.9185   0.04413   0.03632  -0.1049   0.6096   1.0000
   6.500   0.9646   0.04264   0.03488  -0.1061   0.6074   1.0000
   6.750   1.0191   0.04046   0.03277  -0.1080   0.6065   1.0000
   7.000   1.0821   0.03792   0.03034  -0.1111   0.6058   1.0000
   7.250   1.1535   0.03525   0.02777  -0.1157   0.6048   1.0000
   7.500   1.0866   0.04125   0.03380  -0.1057   0.5841   1.0000
   7.750   1.1747   0.03696   0.02966  -0.1112   0.5858   1.0000
   8.000   1.1989   0.03695   0.02974  -0.1104   0.5773   1.0000
   8.250   1.2919   0.03333   0.02626  -0.1180   0.5750   1.0000
   8.500   1.2796   0.03506   0.02808  -0.1125   0.5630   1.0000
   8.750   1.3830   0.03143   0.02458  -0.1222   0.5574   1.0000
   9.000   1.3811   0.03230   0.02554  -0.1175   0.5458   1.0000
   9.250   1.3906   0.03279   0.02614  -0.1146   0.5345   1.0000
   9.500   1.4326   0.03183   0.02527  -0.1160   0.5232   1.0000
   9.750   1.4728   0.03095   0.02446  -0.1171   0.5102   1.0000
  10.000   1.5001   0.03055   0.02410  -0.1164   0.4962   1.0000
  10.250   1.5172   0.03049   0.02408  -0.1143   0.4815   1.0000
  10.500   1.5255   0.03075   0.02441  -0.1110   0.4666   1.0000
  10.750   1.5319   0.03112   0.02483  -0.1075   0.4512   1.0000
  11.000   1.5325   0.03175   0.02554  -0.1034   0.4353   1.0000
  11.250   1.5284   0.03265   0.02650  -0.0989   0.4189   1.0000
  11.500   1.5226   0.03376   0.02767  -0.0945   0.4017   1.0000
  11.750   1.5161   0.03504   0.02900  -0.0904   0.3834   1.0000
  12.000   1.5100   0.03643   0.03038  -0.0866   0.3637   1.0000
  12.250   1.5034   0.03806   0.03197  -0.0830   0.3435   1.0000
  12.500   1.4916   0.04029   0.03422  -0.0795   0.3226   1.0000
  12.750   1.4823   0.04252   0.03633  -0.0765   0.3007   1.0000
  13.000   1.4697   0.04535   0.03918  -0.0737   0.2790   1.0000
  13.250   1.4584   0.04830   0.04203  -0.0714   0.2575   1.0000
  13.500   1.4476   0.05149   0.04520  -0.0695   0.2370   1.0000
  13.750   1.4361   0.05498   0.04867  -0.0679   0.2166   1.0000
  14.000   1.4250   0.05864   0.05224  -0.0666   0.1976   1.0000
  14.250   1.4129   0.06268   0.05628  -0.0656   0.1777   1.0000
  14.500   1.3995   0.06704   0.06058  -0.0649   0.1588   1.0000
  14.750   1.3848   0.07180   0.06526  -0.0646   0.1399   1.0000
  15.000   1.3687   0.07697   0.07037  -0.0645   0.1205   1.0000
  15.250   1.3513   0.08246   0.07570  -0.0647   0.1038   1.0000
  15.500   1.3348   0.08805   0.08118  -0.0650   0.0865   1.0000
  15.750   1.3220   0.09319   0.08621  -0.0653   0.0729   1.0000
  16.000   1.3151   0.09747   0.09040  -0.0654   0.0630   1.0000
  16.250   1.3155   0.10050   0.09325  -0.0652   0.0561   1.0000
  16.500   1.3189   0.10350   0.09641  -0.0652   0.0510   1.0000
  16.750   1.3341   0.10415   0.09683  -0.0638   0.0465   1.0000
  17.000   1.3443   0.10624   0.09915  -0.0633   0.0443   1.0000
  17.250   1.3557   0.10812   0.10119  -0.0628   0.0422   1.0000
  17.500   1.3678   0.10994   0.10311  -0.0624   0.0405   1.0000
  17.750   1.3868   0.11087   0.10402  -0.0614   0.0388   1.0000
  18.000   1.3964   0.11356   0.10687  -0.0612   0.0377   1.0000
  18.250   1.3908   0.11809   0.11169  -0.0625   0.0372   1.0000
  18.500   1.3828   0.12304   0.11693  -0.0643   0.0368   1.0000
  18.750   1.3722   0.12846   0.12264  -0.0665   0.0365   1.0000
  19.000   1.3600   0.13432   0.12877  -0.0692   0.0364   1.0000
  19.250   1.3454   0.14075   0.13546  -0.0725   0.0363   1.0000
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