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S1012 (s1012-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: S1012 (s1012-il)
Reynolds number: 200,000
Max Cl/Cd: 37.72 at α=8.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s1012-il-200000.txt
Download as CSV file: xf-s1012-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -14.250  -0.8614   0.08134   0.07723  -0.0404   1.0000   0.0428
 -14.000  -0.8976   0.07243   0.06815  -0.0458   1.0000   0.0426
 -13.750  -0.9300   0.06553   0.06103  -0.0488   1.0000   0.0424
 -13.500  -0.9578   0.06010   0.05539  -0.0499   1.0000   0.0423
 -13.250  -0.9846   0.05562   0.05065  -0.0495   1.0000   0.0425
 -13.000  -1.0051   0.05194   0.04671  -0.0481   1.0000   0.0425
 -12.750  -1.0239   0.04884   0.04333  -0.0458   1.0000   0.0427
 -12.500  -1.0405   0.04561   0.03984  -0.0429   1.0000   0.0431
 -12.250  -1.0401   0.04274   0.03688  -0.0413   1.0000   0.0441
 -12.000  -1.0326   0.04157   0.03572  -0.0396   1.0000   0.0452
 -11.750  -1.0289   0.04026   0.03432  -0.0372   1.0000   0.0464
 -11.500  -1.0255   0.03867   0.03257  -0.0347   1.0000   0.0476
 -11.250  -1.0212   0.03673   0.03037  -0.0323   1.0000   0.0489
 -11.000  -1.0155   0.03488   0.02819  -0.0299   1.0000   0.0503
 -10.750  -1.0080   0.03340   0.02639  -0.0275   1.0000   0.0515
 -10.500  -0.9909   0.03123   0.02424  -0.0269   1.0000   0.0538
 -10.250  -0.9766   0.03046   0.02345  -0.0253   1.0000   0.0560
 -10.000  -0.9682   0.02964   0.02251  -0.0226   1.0000   0.0582
  -9.750  -0.9704   0.02904   0.02175  -0.0177   1.0000   0.0598
  -9.500  -0.9729   0.02852   0.02103  -0.0128   1.0000   0.0610
  -9.250  -0.9645   0.02694   0.01939  -0.0101   1.0000   0.0633
  -9.000  -0.9572   0.02641   0.01888  -0.0070   1.0000   0.0656
  -8.750  -0.9488   0.02587   0.01826  -0.0040   1.0000   0.0682
  -8.500  -0.9305   0.02529   0.01747  -0.0027   0.9987   0.0716
  -8.250  -0.9032   0.02395   0.01613  -0.0034   0.9966   0.0758
  -8.000  -0.8750   0.02340   0.01553  -0.0042   0.9942   0.0806
  -7.750  -0.8486   0.02293   0.01484  -0.0043   0.9916   0.0846
  -7.500  -0.8225   0.02184   0.01387  -0.0047   0.9894   0.0901
  -7.250  -0.7943   0.02134   0.01327  -0.0052   0.9868   0.0958
  -7.000  -0.7655   0.02049   0.01242  -0.0060   0.9848   0.1016
  -6.750  -0.7363   0.02004   0.01195  -0.0068   0.9830   0.1084
  -6.500  -0.7132   0.01941   0.01131  -0.0063   0.9806   0.1147
  -6.250  -0.6911   0.01901   0.01091  -0.0057   0.9779   0.1219
  -6.000  -0.6665   0.01846   0.01038  -0.0055   0.9754   0.1301
  -5.750  -0.6386   0.01811   0.00999  -0.0059   0.9731   0.1400
  -5.500  -0.6116   0.01759   0.00957  -0.0063   0.9712   0.1519
  -5.250  -0.5855   0.01715   0.00919  -0.0065   0.9696   0.1648
  -5.000  -0.5710   0.01680   0.00890  -0.0043   0.9662   0.1777
  -4.750  -0.5504   0.01641   0.00861  -0.0033   0.9631   0.1958
  -4.500  -0.5286   0.01601   0.00833  -0.0027   0.9608   0.2202
  -4.250  -0.5048   0.01550   0.00806  -0.0025   0.9585   0.2569
  -4.000  -0.4805   0.01486   0.00780  -0.0025   0.9565   0.3229
  -3.750  -0.4735   0.01422   0.00762   0.0009   0.9530   0.4087
  -3.500  -0.4672   0.01337   0.00750   0.0047   0.9490   0.5455
  -3.250  -0.4509   0.01340   0.00831   0.0081   0.9464   0.7019
  -3.000  -0.4246   0.01378   0.00866   0.0088   0.9438   0.7531
  -2.750  -0.3945   0.01426   0.00912   0.0090   0.9419   0.7802
  -2.500  -0.3792   0.01462   0.00945   0.0118   0.9382   0.7987
  -2.250  -0.3604   0.01500   0.00982   0.0142   0.9344   0.8144
  -2.000  -0.3340   0.01542   0.01023   0.0151   0.9313   0.8278
  -1.750  -0.3036   0.01584   0.01062   0.0154   0.9288   0.8398
  -1.500  -0.2692   0.01621   0.01096   0.0147   0.9266   0.8512
  -1.250  -0.2597   0.01643   0.01116   0.0185   0.9206   0.8625
  -1.000  -0.2300   0.01678   0.01150   0.0189   0.9168   0.8708
  -0.750  -0.1961   0.01701   0.01170   0.0182   0.9134   0.8807
  -0.500  -0.1452   0.01748   0.01217   0.0146   0.9117   0.8876
  -0.250  -0.1313   0.01763   0.01232   0.0177   0.9041   0.8977
   0.000   0.0000   0.01853   0.01324   0.0000   0.9066   0.9066
   0.250   0.1310   0.01763   0.01233  -0.0176   0.8977   0.9041
   0.500   0.1451   0.01748   0.01217  -0.0146   0.8876   0.9116
   0.750   0.1958   0.01701   0.01171  -0.0181   0.8807   0.9134
   1.000   0.2301   0.01677   0.01150  -0.0189   0.8708   0.9168
   1.250   0.2600   0.01643   0.01116  -0.0186   0.8628   0.9206
   1.500   0.2690   0.01621   0.01096  -0.0146   0.8512   0.9266
   1.750   0.3036   0.01583   0.01061  -0.0153   0.8396   0.9288
   2.000   0.3342   0.01543   0.01023  -0.0152   0.8280   0.9313
   2.250   0.3603   0.01500   0.00981  -0.0141   0.8143   0.9344
   2.500   0.3792   0.01462   0.00945  -0.0118   0.7987   0.9382
   2.750   0.3945   0.01426   0.00912  -0.0089   0.7803   0.9419
   3.000   0.4246   0.01378   0.00866  -0.0088   0.7533   0.9438
   3.250   0.4508   0.01340   0.00832  -0.0081   0.7028   0.9464
   3.500   0.4673   0.01336   0.00750  -0.0047   0.5471   0.9490
   3.750   0.4735   0.01422   0.00761  -0.0009   0.4093   0.9530
   4.000   0.4805   0.01486   0.00780   0.0025   0.3232   0.9565
   4.250   0.5049   0.01550   0.00806   0.0025   0.2571   0.9585
   4.500   0.5286   0.01601   0.00833   0.0027   0.2200   0.9608
   4.750   0.5504   0.01641   0.00861   0.0033   0.1958   0.9632
   5.000   0.5710   0.01680   0.00890   0.0043   0.1776   0.9662
   5.250   0.5854   0.01715   0.00919   0.0065   0.1648   0.9696
   5.500   0.6117   0.01758   0.00956   0.0063   0.1516   0.9713
   5.750   0.6387   0.01811   0.00999   0.0059   0.1401   0.9731
   6.000   0.6666   0.01846   0.01038   0.0055   0.1300   0.9754
   6.250   0.6911   0.01901   0.01091   0.0057   0.1220   0.9779
   6.500   0.7132   0.01941   0.01131   0.0063   0.1148   0.9806
   6.750   0.7363   0.02004   0.01195   0.0068   0.1084   0.9830
   7.000   0.7656   0.02048   0.01241   0.0060   0.1015   0.9848
   7.250   0.7944   0.02133   0.01326   0.0052   0.0957   0.9868
   7.500   0.8225   0.02182   0.01385   0.0047   0.0900   0.9895
   7.750   0.8487   0.02293   0.01485   0.0043   0.0847   0.9916
   8.000   0.8750   0.02337   0.01550   0.0041   0.0804   0.9942
   8.250   0.9033   0.02395   0.01613   0.0034   0.0758   0.9966
   8.500   0.9306   0.02530   0.01749   0.0027   0.0716   0.9987
   8.750   0.9489   0.02589   0.01829   0.0040   0.0683   1.0000
   9.000   0.9572   0.02641   0.01888   0.0070   0.0655   1.0000
   9.250   0.9644   0.02693   0.01938   0.0101   0.0633   1.0000
   9.500   0.9730   0.02853   0.02104   0.0128   0.0610   1.0000
   9.750   0.9700   0.02900   0.02171   0.0178   0.0597   1.0000
  10.000   0.9680   0.02962   0.02249   0.0226   0.0582   1.0000
  10.250   0.9767   0.03046   0.02345   0.0253   0.0560   1.0000
  10.500   0.9911   0.03120   0.02420   0.0268   0.0538   1.0000
  10.750   1.0081   0.03346   0.02645   0.0274   0.0515   1.0000
  11.000   1.0157   0.03488   0.02819   0.0299   0.0503   1.0000
  11.250   1.0216   0.03677   0.03041   0.0323   0.0490   1.0000
  11.500   1.0257   0.03870   0.03259   0.0347   0.0476   1.0000
  11.750   1.0287   0.04034   0.03441   0.0372   0.0464   1.0000
  12.000   1.0332   0.04155   0.03570   0.0395   0.0453   1.0000
  12.250   1.0400   0.04281   0.03697   0.0412   0.0441   1.0000
  12.500   1.0407   0.04555   0.03978   0.0429   0.0432   1.0000
  12.750   1.0243   0.04885   0.04335   0.0457   0.0427   1.0000
  13.000   1.0059   0.05191   0.04669   0.0480   0.0425   1.0000
  13.250   0.9831   0.05566   0.05070   0.0495   0.0424   1.0000
  13.500   0.9577   0.06023   0.05552   0.0498   0.0423   1.0000
  13.750   0.9297   0.06565   0.06117   0.0487   0.0424   1.0000
  14.000   0.8990   0.07243   0.06813   0.0458   0.0426   1.0000
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