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S9026 (9.5%) (s9026-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: S9026 (9.5%) (s9026-il)
Reynolds number: 100,000
Max Cl/Cd: 33.79 at α=4.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-s9026-il-100000.txt
Download as CSV file: xf-s9026-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S9026 (9.5%)                                    
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -10.750  -0.6652   0.11627   0.11110   0.0110   1.0000   0.1489
 -10.500  -0.7754   0.07898   0.07396  -0.0181   1.0000   0.0802
 -10.250  -0.7837   0.07339   0.06837  -0.0201   1.0000   0.0790
 -10.000  -0.8050   0.06777   0.06269  -0.0221   1.0000   0.0776
  -9.750  -0.8318   0.06234   0.05710  -0.0223   1.0000   0.0762
  -9.500  -0.8536   0.05637   0.05083  -0.0221   1.0000   0.0746
  -9.250  -0.8686   0.05048   0.04447  -0.0211   1.0000   0.0733
  -9.000  -0.8721   0.04559   0.03909  -0.0197   1.0000   0.0731
  -8.750  -0.8661   0.04183   0.03489  -0.0183   1.0000   0.0742
  -8.500  -0.8557   0.03889   0.03152  -0.0169   1.0000   0.0773
  -8.250  -0.8441   0.03595   0.02794  -0.0152   1.0000   0.0799
  -8.000  -0.8286   0.03276   0.02430  -0.0138   1.0000   0.0822
  -7.750  -0.8080   0.03059   0.02207  -0.0130   1.0000   0.0860
  -7.500  -0.7874   0.02882   0.02000  -0.0118   1.0000   0.0917
  -7.250  -0.7663   0.02698   0.01805  -0.0109   1.0000   0.0987
  -7.000  -0.7442   0.02554   0.01632  -0.0098   1.0000   0.1070
  -6.750  -0.7217   0.02402   0.01485  -0.0090   1.0000   0.1169
  -6.500  -0.6995   0.02279   0.01360  -0.0081   1.0000   0.1292
  -6.250  -0.6770   0.02164   0.01245  -0.0071   1.0000   0.1430
  -6.000  -0.6548   0.02064   0.01144  -0.0061   1.0000   0.1594
  -5.750  -0.6326   0.01969   0.01046  -0.0050   1.0000   0.1788
  -5.500  -0.6108   0.01871   0.00965  -0.0040   1.0000   0.1996
  -5.250  -0.5891   0.01784   0.00888  -0.0029   1.0000   0.2252
  -5.000  -0.5679   0.01703   0.00823  -0.0017   1.0000   0.2553
  -4.750  -0.5469   0.01627   0.00764  -0.0004   1.0000   0.2896
  -4.500  -0.5262   0.01559   0.00717   0.0010   1.0000   0.3284
  -4.250  -0.5058   0.01497   0.00674   0.0024   1.0000   0.3713
  -4.000  -0.4855   0.01441   0.00641   0.0039   1.0000   0.4173
  -3.750  -0.4653   0.01392   0.00614   0.0056   1.0000   0.4659
  -3.500  -0.4452   0.01348   0.00593   0.0073   1.0000   0.5153
  -3.250  -0.4254   0.01309   0.00576   0.0092   1.0000   0.5643
  -3.000  -0.4056   0.01278   0.00564   0.0113   1.0000   0.6138
  -2.750  -0.3863   0.01253   0.00559   0.0135   1.0000   0.6621
  -2.500  -0.3673   0.01234   0.00558   0.0159   1.0000   0.7087
  -2.250  -0.3490   0.01222   0.00560   0.0186   1.0000   0.7547
  -2.000  -0.3305   0.01216   0.00566   0.0213   1.0000   0.7993
  -1.750  -0.3100   0.01218   0.00576   0.0238   1.0000   0.8431
  -1.500  -0.2816   0.01231   0.00593   0.0247   1.0000   0.8854
  -1.250  -0.2363   0.01259   0.00616   0.0223   1.0000   0.9227
  -1.000  -0.1724   0.01289   0.00637   0.0160   1.0000   0.9505
  -0.750  -0.0994   0.01303   0.00640   0.0075   1.0000   0.9711
  -0.500  -0.0264   0.01292   0.00622  -0.0015   1.0000   0.9889
  -0.250   0.0188   0.01268   0.00598  -0.0061   1.0000   1.0000
   0.000   0.0000   0.01260   0.00592   0.0000   1.0000   1.0000
   0.250  -0.0188   0.01268   0.00598   0.0061   1.0000   1.0000
   0.500   0.0262   0.01292   0.00622   0.0015   0.9889   1.0000
   0.750   0.0993   0.01303   0.00640  -0.0075   0.9711   1.0000
   1.000   0.1727   0.01289   0.00637  -0.0161   0.9504   1.0000
   1.250   0.2363   0.01259   0.00616  -0.0223   0.9227   1.0000
   1.500   0.2817   0.01231   0.00593  -0.0248   0.8852   1.0000
   1.750   0.3100   0.01218   0.00576  -0.0238   0.8430   1.0000
   2.000   0.3306   0.01216   0.00566  -0.0214   0.7994   1.0000
   2.250   0.3491   0.01222   0.00560  -0.0186   0.7547   1.0000
   2.500   0.3675   0.01234   0.00559  -0.0160   0.7088   1.0000
   2.750   0.3864   0.01253   0.00559  -0.0135   0.6621   1.0000
   3.000   0.4057   0.01278   0.00565  -0.0113   0.6137   1.0000
   3.250   0.4255   0.01309   0.00576  -0.0093   0.5643   1.0000
   3.500   0.4454   0.01348   0.00593  -0.0073   0.5152   1.0000
   3.750   0.4655   0.01392   0.00614  -0.0056   0.4659   1.0000
   4.000   0.4856   0.01441   0.00641  -0.0040   0.4172   1.0000
   4.250   0.5059   0.01497   0.00674  -0.0024   0.3711   1.0000
   4.500   0.5263   0.01559   0.00717  -0.0010   0.3283   1.0000
   4.750   0.5470   0.01627   0.00764   0.0004   0.2895   1.0000
   5.000   0.5680   0.01703   0.00823   0.0016   0.2552   1.0000
   5.250   0.5892   0.01784   0.00888   0.0028   0.2252   1.0000
   5.500   0.6109   0.01871   0.00965   0.0040   0.1996   1.0000
   5.750   0.6327   0.01969   0.01046   0.0050   0.1788   1.0000
   6.000   0.6548   0.02064   0.01144   0.0061   0.1594   1.0000
   6.250   0.6771   0.02165   0.01245   0.0071   0.1430   1.0000
   6.500   0.6994   0.02278   0.01360   0.0080   0.1291   1.0000
   6.750   0.7217   0.02402   0.01485   0.0090   0.1168   1.0000
   7.000   0.7441   0.02553   0.01632   0.0098   0.1069   1.0000
   7.250   0.7662   0.02698   0.01806   0.0109   0.0987   1.0000
   7.500   0.7873   0.02884   0.02002   0.0119   0.0917   1.0000
   7.750   0.8079   0.03059   0.02206   0.0130   0.0860   1.0000
   8.000   0.8285   0.03277   0.02430   0.0138   0.0822   1.0000
   8.250   0.8440   0.03594   0.02793   0.0152   0.0799   1.0000
   8.500   0.8556   0.03889   0.03152   0.0169   0.0773   1.0000
   8.750   0.8658   0.04187   0.03495   0.0184   0.0743   1.0000
   9.000   0.8720   0.04556   0.03905   0.0198   0.0731   1.0000
   9.250   0.8685   0.05045   0.04445   0.0212   0.0733   1.0000
   9.500   0.8534   0.05637   0.05083   0.0221   0.0746   1.0000
   9.750   0.8318   0.06232   0.05708   0.0223   0.0762   1.0000
  10.000   0.8060   0.06769   0.06260   0.0222   0.0777   1.0000
  10.250   0.7826   0.07350   0.06848   0.0200   0.0790   1.0000
  10.500   0.7760   0.07892   0.07390   0.0182   0.0802   1.0000
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