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SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)
Reynolds number: 50,000
Max Cl/Cd: 27.15 at α=5.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc1094r8-il-50000-n5.txt
Download as CSV file: xf-sc1094r8-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY SC1094 R8 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.500  -0.4143   0.10405   0.09732  -0.0028   1.0000   0.1384
  -8.250  -0.4303   0.10082   0.09418  -0.0068   1.0000   0.1437
  -8.000  -0.4323   0.09660   0.09004  -0.0086   1.0000   0.1452
  -7.750  -0.4194   0.09254   0.08601  -0.0078   1.0000   0.1471
  -7.500  -0.4159   0.08867   0.08220  -0.0086   1.0000   0.1489
  -7.250  -0.4930   0.07879   0.07170  -0.0210   1.0000   0.0775
  -7.000  -0.4836   0.07410   0.06697  -0.0221   1.0000   0.0702
  -6.750  -0.4797   0.06853   0.06120  -0.0250   1.0000   0.0651
  -6.500  -0.4679   0.06508   0.05769  -0.0253   1.0000   0.0635
  -6.250  -0.4575   0.06115   0.05362  -0.0261   1.0000   0.0622
  -6.000  -0.4461   0.05727   0.04953  -0.0268   1.0000   0.0615
  -5.750  -0.4329   0.05372   0.04575  -0.0270   1.0000   0.0615
  -5.500  -0.4183   0.05040   0.04218  -0.0269   1.0000   0.0616
  -5.250  -0.4026   0.04722   0.03871  -0.0265   1.0000   0.0615
  -5.000  -0.3857   0.04413   0.03528  -0.0259   1.0000   0.0610
  -4.750  -0.3677   0.04119   0.03195  -0.0251   1.0000   0.0604
  -4.500  -0.3486   0.03860   0.02900  -0.0242   1.0000   0.0601
  -4.250  -0.3286   0.03633   0.02642  -0.0231   1.0000   0.0603
  -4.000  -0.3081   0.03447   0.02434  -0.0221   1.0000   0.0614
  -3.750  -0.2869   0.03271   0.02229  -0.0211   1.0000   0.0632
  -3.500  -0.2645   0.03096   0.02014  -0.0200   1.0000   0.0650
  -3.250  -0.2427   0.02958   0.01870  -0.0190   1.0000   0.0664
  -3.000  -0.2201   0.02824   0.01720  -0.0179   1.0000   0.0678
  -2.750  -0.1970   0.02705   0.01579  -0.0168   1.0000   0.0702
  -2.500  -0.1746   0.02608   0.01483  -0.0159   1.0000   0.0735
  -2.250  -0.1514   0.02518   0.01380  -0.0147   1.0000   0.0772
  -2.000  -0.1285   0.02438   0.01304  -0.0137   1.0000   0.0805
  -1.750  -0.1056   0.02374   0.01236  -0.0127   1.0000   0.0861
  -1.500  -0.0832   0.02319   0.01178  -0.0118   1.0000   0.0928
  -1.250  -0.0544   0.02259   0.01123  -0.0123   0.9962   0.1024
  -1.000  -0.0055   0.02177   0.01054  -0.0166   0.9810   0.1256
  -0.750   0.0416   0.02025   0.00975  -0.0209   0.9669   0.2269
  -0.500   0.1015   0.01788   0.00974  -0.0238   0.9573   1.0000
  -0.250   0.1519   0.01792   0.00947  -0.0279   0.9372   1.0000
   0.000   0.1931   0.01789   0.00924  -0.0300   0.9117   1.0000
   0.250   0.2343   0.01779   0.00897  -0.0317   0.8833   1.0000
   0.500   0.2673   0.01767   0.00870  -0.0316   0.8471   1.0000
   0.750   0.2967   0.01755   0.00841  -0.0306   0.8062   1.0000
   1.000   0.3224   0.01749   0.00815  -0.0289   0.7606   1.0000
   1.250   0.3464   0.01750   0.00792  -0.0270   0.7109   1.0000
   1.500   0.3695   0.01761   0.00773  -0.0249   0.6568   1.0000
   1.750   0.3918   0.01783   0.00759  -0.0229   0.5997   1.0000
   2.000   0.4136   0.01819   0.00755  -0.0210   0.5430   1.0000
   2.250   0.4354   0.01867   0.00762  -0.0194   0.4903   1.0000
   2.500   0.4575   0.01921   0.00780  -0.0180   0.4431   1.0000
   2.750   0.4799   0.01980   0.00807  -0.0169   0.4017   1.0000
   3.000   0.5029   0.02043   0.00840  -0.0160   0.3661   1.0000
   3.250   0.5266   0.02109   0.00880  -0.0153   0.3351   1.0000
   3.500   0.5508   0.02175   0.00924  -0.0147   0.3088   1.0000
   3.750   0.5753   0.02242   0.00975  -0.0142   0.2860   1.0000
   4.000   0.6001   0.02310   0.01030  -0.0137   0.2673   1.0000
   4.250   0.6249   0.02380   0.01086  -0.0132   0.2516   1.0000
   4.750   0.6750   0.02524   0.01215  -0.0123   0.2266   1.0000
   5.000   0.7001   0.02602   0.01285  -0.0119   0.2170   1.0000
   5.250   0.7252   0.02681   0.01360  -0.0115   0.2082   1.0000
   5.500   0.7503   0.02768   0.01442  -0.0111   0.2007   1.0000
   5.750   0.7753   0.02856   0.01536  -0.0107   0.1936   1.0000
   6.000   0.8002   0.02949   0.01615  -0.0103   0.1884   1.0000
   6.250   0.8248   0.03057   0.01743  -0.0099   0.1823   1.0000
   6.500   0.8490   0.03159   0.01848  -0.0095   0.1771   1.0000
   6.750   0.8735   0.03264   0.01944  -0.0092   0.1732   1.0000
   7.000   0.8966   0.03403   0.02110  -0.0088   0.1690   1.0000
   7.250   0.9193   0.03539   0.02264  -0.0083   0.1649   1.0000
   7.500   0.9421   0.03663   0.02395  -0.0079   0.1613   1.0000
   7.750   0.9655   0.03787   0.02513  -0.0076   0.1584   1.0000
   8.000   0.9843   0.03983   0.02747  -0.0070   0.1554   1.0000
   8.250   1.0024   0.04184   0.02981  -0.0064   0.1526   1.0000
   8.500   1.0202   0.04375   0.03196  -0.0058   0.1499   1.0000
   8.750   1.0387   0.04546   0.03381  -0.0053   0.1474   1.0000
   9.000   1.0586   0.04704   0.03542  -0.0048   0.1453   1.0000
   9.250   1.0692   0.04979   0.03851  -0.0041   0.1433   1.0000
   9.500   1.0722   0.05334   0.04254  -0.0032   0.1417   1.0000
   9.750   1.0705   0.05722   0.04684  -0.0024   0.1401   1.0000
  10.000   1.0631   0.06144   0.05141  -0.0017   0.1386   1.0000
  10.250   1.0477   0.06621   0.05648  -0.0014   0.1373   1.0000
  10.500   1.0125   0.07260   0.06313  -0.0018   0.1365   1.0000
  10.750   0.9130   0.09201   0.08276  -0.0149   0.1365   1.0000
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