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SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il)
Reynolds number: 50,000
Max Cl/Cd: 23.59 at α=3°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1012r8-il-50000.txt
Download as CSV file: xf-sc1012r8-il-50000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY SC1012R8 AIRFOIL                       
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.050 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.250  -0.3790   0.10711   0.10035  -0.0004   1.0000   0.2533
  -8.000  -0.3736   0.10360   0.09692  -0.0005   1.0000   0.2627
  -7.750  -0.3969   0.10284   0.09630  -0.0025   1.0000   0.2760
  -7.500  -0.3633   0.09793   0.09140   0.0001   1.0000   0.2908
  -7.250  -0.3538   0.09471   0.08826   0.0009   1.0000   0.3059
  -7.000  -0.3480   0.09188   0.08552   0.0018   1.0000   0.3237
  -6.750  -0.3418   0.08923   0.08296   0.0031   1.0000   0.3446
  -6.500  -0.3487   0.08747   0.08132   0.0046   1.0000   0.3690
  -6.250  -0.3236   0.08402   0.07793   0.0073   1.0000   0.3986
  -6.000  -0.3108   0.08160   0.07559   0.0102   1.0000   0.4353
  -5.750  -0.2931   0.07932   0.07339   0.0137   1.0000   0.4797
  -5.500  -0.3040   0.07884   0.07306   0.0187   1.0000   0.5235
  -5.250  -0.2378   0.07370   0.06788   0.0200   1.0000   0.5882
  -5.000  -0.2084   0.07117   0.06541   0.0228   1.0000   0.6537
  -4.750  -0.1570   0.06685   0.06111   0.0223   1.0000   0.7257
  -3.500  -0.3364   0.04472   0.03726  -0.0136   1.0000   0.1945
  -3.250  -0.3121   0.04168   0.03374  -0.0139   1.0000   0.1721
  -3.000  -0.2870   0.03952   0.03095  -0.0137   1.0000   0.1581
  -2.750  -0.2654   0.03751   0.02872  -0.0133   1.0000   0.1552
  -2.500  -0.2427   0.03588   0.02682  -0.0130   1.0000   0.1539
  -2.250  -0.2190   0.03445   0.02515  -0.0127   1.0000   0.1530
  -2.000  -0.1946   0.03321   0.02366  -0.0124   1.0000   0.1519
  -1.750  -0.1711   0.03223   0.02248  -0.0122   1.0000   0.1525
  -1.500  -0.1489   0.03158   0.02167  -0.0119   1.0000   0.1564
  -1.250  -0.1276   0.03124   0.02112  -0.0115   1.0000   0.1605
  -1.000  -0.0817   0.03023   0.02023  -0.0153   0.9910   0.1689
  -0.750  -0.0073   0.02936   0.01941  -0.0230   0.9694   0.1935
  -0.500   0.0605   0.02789   0.01836  -0.0297   0.9455   0.2530
  -0.250   0.1500   0.02494   0.01777  -0.0353   0.9236   1.0000
   0.000   0.2491   0.02460   0.01702  -0.0464   0.8884   1.0000
   0.250   0.3224   0.02371   0.01591  -0.0516   0.8504   1.0000
   0.500   0.3666   0.02290   0.01491  -0.0515   0.8118   1.0000
   0.750   0.3954   0.02231   0.01413  -0.0488   0.7724   1.0000
   1.000   0.4172   0.02196   0.01357  -0.0455   0.7311   1.0000
   1.250   0.4381   0.02174   0.01308  -0.0421   0.6897   1.0000
   1.500   0.4588   0.02167   0.01270  -0.0389   0.6487   1.0000
   1.750   0.4794   0.02179   0.01246  -0.0360   0.6083   1.0000
   2.000   0.5003   0.02211   0.01240  -0.0334   0.5690   1.0000
   2.250   0.5213   0.02260   0.01253  -0.0312   0.5310   1.0000
   2.500   0.5425   0.02327   0.01287  -0.0293   0.4952   1.0000
   2.750   0.5640   0.02406   0.01339  -0.0277   0.4625   1.0000
   3.000   0.5871   0.02489   0.01384  -0.0263   0.4358   1.0000
   3.250   0.6091   0.02586   0.01469  -0.0251   0.4102   1.0000
   3.500   0.6320   0.02683   0.01549  -0.0240   0.3889   1.0000
   3.750   0.6553   0.02789   0.01640  -0.0231   0.3709   1.0000
   4.000   0.6786   0.02899   0.01738  -0.0223   0.3551   1.0000
   4.250   0.7029   0.03009   0.01828  -0.0215   0.3418   1.0000
   4.500   0.7254   0.03135   0.01959  -0.0208   0.3290   1.0000
   4.750   0.7474   0.03278   0.02107  -0.0201   0.3180   1.0000
   5.000   0.7718   0.03394   0.02207  -0.0194   0.3083   1.0000
   5.250   0.7909   0.03585   0.02423  -0.0187   0.3001   1.0000
   5.500   0.8133   0.03733   0.02571  -0.0181   0.2925   1.0000
   5.750   0.8333   0.03919   0.02763  -0.0174   0.2859   1.0000
   6.000   0.8480   0.04147   0.03020  -0.0166   0.2791   1.0000
   6.250   0.8699   0.04310   0.03180  -0.0160   0.2737   1.0000
   6.500   0.8891   0.04540   0.03413  -0.0155   0.2700   1.0000
   6.750   0.8918   0.04921   0.03843  -0.0145   0.2670   1.0000
   7.000   0.8903   0.05345   0.04305  -0.0138   0.2642   1.0000
   7.250   0.8820   0.05836   0.04827  -0.0133   0.2623   1.0000
   7.500   0.8521   0.06569   0.05593  -0.0137   0.2628   1.0000
   7.750   0.8038   0.07544   0.06587  -0.0161   0.2669   1.0000
   8.000   0.7800   0.08382   0.07432  -0.0195   0.2719   1.0000
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