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S1012 (s1012-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S1012 (s1012-il)
Reynolds number: 50,000
Max Cl/Cd: 25.54 at α=3.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s1012-il-50000-n5.txt
Download as CSV file: xf-s1012-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S1012                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.6653   0.09990   0.09214  -0.0281   1.0000   0.0808
 -12.000  -0.7025   0.08749   0.07974  -0.0364   1.0000   0.0805
 -11.750  -0.7467   0.07740   0.06957  -0.0424   1.0000   0.0795
 -11.500  -0.7848   0.07041   0.06243  -0.0447   1.0000   0.0790
 -11.250  -0.8147   0.06535   0.05719  -0.0446   1.0000   0.0791
 -11.000  -0.8385   0.06141   0.05304  -0.0429   1.0000   0.0797
 -10.750  -0.8584   0.05811   0.04950  -0.0401   1.0000   0.0807
 -10.500  -0.8740   0.05486   0.04592  -0.0371   1.0000   0.0823
 -10.250  -0.8869   0.05163   0.04221  -0.0339   1.0000   0.0841
 -10.000  -0.8792   0.04956   0.04008  -0.0323   1.0000   0.0867
  -9.750  -0.8707   0.04769   0.03810  -0.0305   1.0000   0.0893
  -9.500  -0.8649   0.04567   0.03585  -0.0283   1.0000   0.0925
  -9.250  -0.8619   0.04348   0.03324  -0.0255   1.0000   0.0963
  -9.000  -0.8524   0.04171   0.03133  -0.0234   1.0000   0.0998
  -8.750  -0.8406   0.04033   0.02987  -0.0213   1.0000   0.1033
  -8.500  -0.8320   0.03890   0.02820  -0.0187   1.0000   0.1079
  -8.250  -0.8230   0.03743   0.02644  -0.0160   1.0000   0.1126
  -8.000  -0.8097   0.03633   0.02537  -0.0140   1.0000   0.1170
  -7.750  -0.7972   0.03515   0.02400  -0.0117   1.0000   0.1224
  -7.500  -0.7836   0.03402   0.02271  -0.0096   1.0000   0.1283
  -7.250  -0.7691   0.03308   0.02174  -0.0076   1.0000   0.1346
  -7.000  -0.7521   0.03204   0.02048  -0.0059   1.0000   0.1417
  -6.750  -0.7358   0.03120   0.01969  -0.0041   1.0000   0.1493
  -6.500  -0.7174   0.03034   0.01872  -0.0026   1.0000   0.1583
  -6.250  -0.6990   0.02957   0.01790  -0.0011   1.0000   0.1679
  -6.000  -0.6808   0.02884   0.01718   0.0004   1.0000   0.1790
  -5.750  -0.6624   0.02814   0.01646   0.0020   1.0000   0.1913
  -5.500  -0.6458   0.02746   0.01579   0.0037   1.0000   0.2057
  -5.250  -0.6305   0.02679   0.01516   0.0057   1.0000   0.2219
  -5.000  -0.6163   0.02610   0.01456   0.0078   1.0000   0.2408
  -4.750  -0.6029   0.02542   0.01396   0.0100   1.0000   0.2652
  -4.500  -0.5912   0.02465   0.01341   0.0124   1.0000   0.2947
  -4.000  -0.5718   0.02287   0.01236   0.0180   1.0000   0.3989
  -3.750  -0.5628   0.02204   0.01227   0.0217   1.0000   0.5016
  -3.500  -0.5244   0.02320   0.01431   0.0240   1.0000   0.6647
  -3.250  -0.5173   0.02346   0.01445   0.0284   1.0000   0.7287
  -3.000  -0.5108   0.02364   0.01447   0.0327   1.0000   0.7713
  -2.750  -0.4951   0.02407   0.01477   0.0359   1.0000   0.8039
  -2.500  -0.4773   0.02447   0.01504   0.0387   1.0000   0.8321
  -2.250  -0.4422   0.02516   0.01558   0.0387   1.0000   0.8565
  -2.000  -0.4129   0.02560   0.01588   0.0392   1.0000   0.8799
  -1.750  -0.3521   0.02641   0.01651   0.0342   1.0000   0.9019
  -1.500  -0.2846   0.02709   0.01701   0.0274   1.0000   0.9265
  -1.250  -0.2119   0.02743   0.01720   0.0191   1.0000   0.9454
  -1.000  -0.1668   0.02745   0.01713   0.0151   1.0000   0.9587
  -0.750  -0.1296   0.02742   0.01703   0.0124   0.9998   0.9691
  -0.500  -0.0837   0.02733   0.01689   0.0078   0.9962   0.9756
  -0.250  -0.0431   0.02736   0.01689   0.0042   0.9921   0.9823
   0.000   0.0001   0.02728   0.01680   0.0000   0.9872   0.9872
   0.250   0.0432   0.02736   0.01688  -0.0042   0.9823   0.9921
   0.500   0.0837   0.02733   0.01689  -0.0078   0.9756   0.9962
   0.750   0.1296   0.02742   0.01702  -0.0124   0.9692   0.9998
   1.000   0.1667   0.02745   0.01713  -0.0151   0.9588   1.0000
   1.250   0.2118   0.02742   0.01720  -0.0191   0.9455   1.0000
   1.500   0.2843   0.02708   0.01701  -0.0274   0.9265   1.0000
   1.750   0.3517   0.02641   0.01651  -0.0341   0.9021   1.0000
   2.000   0.4124   0.02560   0.01588  -0.0391   0.8800   1.0000
   2.250   0.4423   0.02515   0.01557  -0.0387   0.8564   1.0000
   2.500   0.4773   0.02447   0.01505  -0.0387   0.8323   1.0000
   2.750   0.4951   0.02407   0.01477  -0.0359   0.8040   1.0000
   3.000   0.5107   0.02364   0.01448  -0.0327   0.7716   1.0000
   3.250   0.5174   0.02346   0.01444  -0.0285   0.7294   1.0000
   3.500   0.5245   0.02319   0.01429  -0.0240   0.6642   1.0000
   3.750   0.5627   0.02203   0.01227  -0.0217   0.5017   1.0000
   4.000   0.5717   0.02287   0.01236  -0.0180   0.3989   1.0000
   4.250   0.5808   0.02380   0.01286  -0.0150   0.3362   1.0000
   4.500   0.5912   0.02464   0.01341  -0.0124   0.2947   1.0000
   4.750   0.6029   0.02541   0.01396  -0.0100   0.2652   1.0000
   5.000   0.6162   0.02610   0.01456  -0.0077   0.2406   1.0000
   5.250   0.6305   0.02679   0.01516  -0.0057   0.2220   1.0000
   5.500   0.6457   0.02746   0.01579  -0.0037   0.2055   1.0000
   5.750   0.6624   0.02813   0.01645  -0.0020   0.1914   1.0000
   6.000   0.6807   0.02883   0.01718  -0.0004   0.1789   1.0000
   6.250   0.6989   0.02957   0.01789   0.0011   0.1679   1.0000
   6.500   0.7174   0.03034   0.01872   0.0026   0.1583   1.0000
   6.750   0.7358   0.03119   0.01968   0.0041   0.1493   1.0000
   7.000   0.7520   0.03204   0.02047   0.0059   0.1417   1.0000
   7.250   0.7690   0.03308   0.02173   0.0076   0.1345   1.0000
   7.500   0.7836   0.03402   0.02270   0.0096   0.1283   1.0000
   7.750   0.7974   0.03516   0.02401   0.0117   0.1225   1.0000
   8.000   0.8096   0.03632   0.02537   0.0140   0.1170   1.0000
   8.250   0.8230   0.03742   0.02644   0.0161   0.1127   1.0000
   8.500   0.8319   0.03890   0.02820   0.0187   0.1078   1.0000
   8.750   0.8407   0.04034   0.02988   0.0213   0.1034   1.0000
   9.000   0.8524   0.04170   0.03131   0.0234   0.0997   1.0000
   9.250   0.8619   0.04348   0.03325   0.0255   0.0963   1.0000
   9.500   0.8650   0.04567   0.03585   0.0283   0.0926   1.0000
   9.750   0.8708   0.04769   0.03810   0.0305   0.0893   1.0000
  10.000   0.8795   0.04954   0.04006   0.0322   0.0866   1.0000
  10.250   0.8869   0.05162   0.04220   0.0339   0.0841   1.0000
  10.500   0.8742   0.05487   0.04593   0.0371   0.0823   1.0000
  10.750   0.8585   0.05813   0.04952   0.0401   0.0807   1.0000
  11.000   0.8387   0.06141   0.05303   0.0429   0.0797   1.0000
  11.250   0.8151   0.06536   0.05719   0.0446   0.0791   1.0000
  11.500   0.7850   0.07044   0.06246   0.0446   0.0790   1.0000
  11.750   0.7470   0.07745   0.06962   0.0423   0.0795   1.0000
  12.000   0.7033   0.08747   0.07972   0.0363   0.0805   1.0000
  12.250   0.6657   0.10003   0.09226   0.0279   0.0808   1.0000
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