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S2046 (s2046-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: S2046 (s2046-il)
Reynolds number: 50,000
Max Cl/Cd: 40.1 at α=5.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-s2046-il-50000-n5.txt
Download as CSV file: xf-s2046-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: S2046                                           
  
 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
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4582   0.08343   0.07630  -0.0399   1.0000   0.0487
  -8.250  -0.4635   0.07909   0.07204  -0.0418   1.0000   0.0486
  -8.000  -0.4683   0.07378   0.06680  -0.0457   1.0000   0.0485
  -7.750  -0.4735   0.06874   0.06177  -0.0492   1.0000   0.0483
  -7.500  -0.4785   0.06372   0.05668  -0.0523   1.0000   0.0484
  -7.250  -0.4813   0.05863   0.05142  -0.0552   1.0000   0.0485
  -7.000  -0.4787   0.05415   0.04676  -0.0570   1.0000   0.0492
  -6.750  -0.4686   0.05178   0.04439  -0.0568   1.0000   0.0507
  -6.500  -0.4585   0.04828   0.04067  -0.0577   1.0000   0.0519
  -6.250  -0.4458   0.04424   0.03623  -0.0590   1.0000   0.0526
  -6.000  -0.4294   0.04047   0.03202  -0.0601   1.0000   0.0535
  -5.750  -0.4102   0.03706   0.02814  -0.0608   1.0000   0.0550
  -5.500  -0.3887   0.03398   0.02455  -0.0611   1.0000   0.0571
  -5.250  -0.3652   0.03129   0.02123  -0.0612   1.0000   0.0608
  -5.000  -0.3447   0.02995   0.01991  -0.0608   1.0000   0.0660
  -4.750  -0.3211   0.02815   0.01766  -0.0603   1.0000   0.0727
  -4.500  -0.2993   0.02684   0.01633  -0.0598   1.0000   0.0808
  -4.250  -0.2766   0.02565   0.01501  -0.0592   1.0000   0.0931
  -4.000  -0.2539   0.02464   0.01391  -0.0587   1.0000   0.1092
  -3.750  -0.2310   0.02371   0.01287  -0.0581   1.0000   0.1277
  -3.500  -0.2086   0.02285   0.01197  -0.0574   1.0000   0.1468
  -3.250  -0.1854   0.02204   0.01117  -0.0570   1.0000   0.1664
  -3.000  -0.1607   0.02133   0.01050  -0.0569   1.0000   0.1945
  -2.750  -0.1352   0.02061   0.00989  -0.0572   1.0000   0.2333
  -2.500  -0.1091   0.01976   0.00947  -0.0577   1.0000   0.3081
  -2.250  -0.0866   0.01917   0.00959  -0.0570   1.0000   0.4505
  -2.000  -0.0674   0.01911   0.00978  -0.0552   1.0000   0.5556
  -1.750  -0.0493   0.01918   0.00992  -0.0532   1.0000   0.6234
  -1.500  -0.0249   0.01931   0.01009  -0.0523   0.9955   0.6823
  -1.250   0.0046   0.01944   0.01022  -0.0522   0.9865   0.7392
  -1.000   0.0315   0.01945   0.01028  -0.0515   0.9771   0.7954
  -0.750   0.0575   0.01928   0.01022  -0.0503   0.9677   0.8608
  -0.500   0.1017   0.01900   0.00994  -0.0535   0.9570   1.0000
  -0.250   0.1429   0.01922   0.00993  -0.0570   0.9466   1.0000
   0.000   0.1851   0.01946   0.00996  -0.0606   0.9362   1.0000
   0.250   0.2297   0.01968   0.01001  -0.0643   0.9263   1.0000
   0.500   0.2700   0.01986   0.01006  -0.0670   0.9143   1.0000
   0.750   0.3095   0.02002   0.01012  -0.0694   0.9019   1.0000
   1.000   0.3490   0.02015   0.01018  -0.0717   0.8893   1.0000
   1.250   0.3877   0.02025   0.01024  -0.0737   0.8762   1.0000
   1.500   0.4245   0.02032   0.01028  -0.0752   0.8624   1.0000
   1.750   0.4603   0.02035   0.01031  -0.0763   0.8479   1.0000
   2.000   0.4952   0.02036   0.01035  -0.0772   0.8329   1.0000
   2.250   0.5292   0.02035   0.01037  -0.0778   0.8171   1.0000
   2.500   0.5626   0.02032   0.01037  -0.0782   0.8005   1.0000
   2.750   0.5958   0.02026   0.01037  -0.0784   0.7831   1.0000
   3.000   0.6251   0.02027   0.01045  -0.0780   0.7626   1.0000
   3.250   0.6554   0.02024   0.01046  -0.0776   0.7414   1.0000
   3.500   0.6844   0.02024   0.01052  -0.0770   0.7178   1.0000
   3.750   0.7141   0.02021   0.01056  -0.0763   0.6931   1.0000
   4.000   0.7420   0.02026   0.01064  -0.0754   0.6650   1.0000
   4.250   0.7690   0.02037   0.01076  -0.0745   0.6341   1.0000
   4.500   0.7951   0.02056   0.01099  -0.0734   0.6001   1.0000
   4.750   0.8209   0.02080   0.01116  -0.0722   0.5643   1.0000
   5.000   0.8451   0.02117   0.01144  -0.0709   0.5254   1.0000
   5.250   0.8681   0.02165   0.01177  -0.0695   0.4849   1.0000
   5.500   0.8898   0.02226   0.01220  -0.0681   0.4438   1.0000
   5.750   0.9104   0.02298   0.01282  -0.0667   0.4028   1.0000
   6.000   0.9303   0.02377   0.01350  -0.0653   0.3626   1.0000
   6.250   0.9496   0.02464   0.01425  -0.0640   0.3238   1.0000
   6.500   0.9679   0.02560   0.01510  -0.0627   0.2839   1.0000
   6.750   0.9859   0.02667   0.01611  -0.0614   0.2439   1.0000
   7.000   1.0032   0.02790   0.01719  -0.0602   0.2074   1.0000
   7.250   1.0209   0.02928   0.01844  -0.0590   0.1779   1.0000
   7.500   1.0381   0.03074   0.01976  -0.0578   0.1550   1.0000
   7.750   1.0570   0.03225   0.02125  -0.0568   0.1383   1.0000
   8.000   1.0760   0.03380   0.02283  -0.0558   0.1255   1.0000
   8.250   1.0946   0.03535   0.02440  -0.0548   0.1143   1.0000
   8.500   1.1158   0.03704   0.02628  -0.0539   0.1056   1.0000
   8.750   1.1366   0.03887   0.02808  -0.0531   0.0994   1.0000
   9.000   1.1565   0.04075   0.03029  -0.0522   0.0923   1.0000
   9.250   1.1754   0.04267   0.03212  -0.0515   0.0867   1.0000
   9.500   1.1945   0.04514   0.03512  -0.0505   0.0824   1.0000
   9.750   1.2107   0.04753   0.03778  -0.0494   0.0782   1.0000
  10.000   1.2279   0.04980   0.03999  -0.0488   0.0741   1.0000
  10.250   1.2337   0.05281   0.04359  -0.0469   0.0709   1.0000
  10.500   1.2391   0.05615   0.04737  -0.0453   0.0686   1.0000
  10.750   1.2412   0.05946   0.05103  -0.0436   0.0665   1.0000
  11.000   1.2422   0.06240   0.05419  -0.0420   0.0643   1.0000
  11.250   1.2488   0.06511   0.05688  -0.0410   0.0619   1.0000
  11.500   1.2318   0.06892   0.06104  -0.0387   0.0611   1.0000
  11.750   1.2110   0.07329   0.06576  -0.0375   0.0605   1.0000
  12.000   1.1883   0.07838   0.07115  -0.0376   0.0603   1.0000
  12.250   1.1636   0.08434   0.07736  -0.0393   0.0603   1.0000
  12.500   1.1371   0.09139   0.08462  -0.0425   0.0605   1.0000
  12.750   1.1100   0.09961   0.09300  -0.0472   0.0609   1.0000
  13.000   1.0831   0.10907   0.10257  -0.0532   0.0614   1.0000
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