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SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il)
Reynolds number: 50,000
Max Cl/Cd: 26.73 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc1012r8-il-50000-n5.txt
Download as CSV file: xf-sc1012r8-il-50000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3940   0.10854   0.10148  -0.0084   1.0000   0.1370
  -8.500  -0.4227   0.10623   0.09930  -0.0157   1.0000   0.1425
  -7.750  -0.4297   0.08421   0.07720  -0.0293   1.0000   0.0750
  -7.500  -0.4182   0.08125   0.07428  -0.0284   1.0000   0.0726
  -7.250  -0.4176   0.07743   0.07048  -0.0291   1.0000   0.0706
  -7.000  -0.4378   0.07086   0.06360  -0.0323   1.0000   0.0654
  -6.750  -0.4325   0.06793   0.06069  -0.0314   1.0000   0.0647
  -6.500  -0.4298   0.06490   0.05762  -0.0303   1.0000   0.0640
  -6.250  -0.4276   0.06183   0.05448  -0.0291   1.0000   0.0633
  -6.000  -0.4246   0.05876   0.05128  -0.0278   1.0000   0.0626
  -5.750  -0.4203   0.05577   0.04812  -0.0264   1.0000   0.0622
  -5.500  -0.4142   0.05294   0.04509  -0.0249   1.0000   0.0623
  -5.250  -0.4061   0.05024   0.04215  -0.0234   1.0000   0.0627
  -5.000  -0.3961   0.04766   0.03930  -0.0220   1.0000   0.0633
  -4.750  -0.3840   0.04519   0.03653  -0.0206   1.0000   0.0638
  -4.500  -0.3700   0.04285   0.03388  -0.0192   1.0000   0.0641
  -4.250  -0.3542   0.04067   0.03140  -0.0180   1.0000   0.0642
  -4.000  -0.3368   0.03864   0.02905  -0.0168   1.0000   0.0645
  -3.750  -0.3180   0.03677   0.02685  -0.0158   1.0000   0.0649
  -3.500  -0.2924   0.03509   0.02493  -0.0159   0.9975   0.0663
  -3.250  -0.2489   0.03357   0.02332  -0.0194   0.9875   0.0694
  -3.000  -0.2027   0.03189   0.02130  -0.0227   0.9768   0.0724
  -2.750  -0.1552   0.03028   0.01936  -0.0259   0.9654   0.0748
  -2.500  -0.1098   0.02910   0.01825  -0.0290   0.9524   0.0796
  -2.250  -0.0644   0.02799   0.01698  -0.0315   0.9392   0.0853
  -2.000  -0.0207   0.02696   0.01604  -0.0338   0.9256   0.0915
  -1.750   0.0208   0.02606   0.01514  -0.0357   0.9109   0.1010
  -1.500   0.0583   0.02522   0.01431  -0.0368   0.8949   0.1133
  -1.250   0.0927   0.02435   0.01355  -0.0374   0.8776   0.1329
  -1.000   0.1246   0.02334   0.01277  -0.0376   0.8589   0.1702
  -0.750   0.1385   0.02045   0.01244  -0.0343   0.8414   0.6294
  -0.500   0.2598   0.01993   0.01207  -0.0455   0.8190   1.0000
  -0.250   0.2836   0.01972   0.01159  -0.0438   0.7882   1.0000
   0.000   0.3056   0.01952   0.01114  -0.0417   0.7537   1.0000
   0.250   0.3262   0.01939   0.01074  -0.0394   0.7156   1.0000
   0.500   0.3463   0.01934   0.01040  -0.0371   0.6749   1.0000
   0.750   0.3665   0.01936   0.01011  -0.0349   0.6336   1.0000
   1.000   0.3866   0.01948   0.00988  -0.0327   0.5926   1.0000
   1.250   0.4065   0.01970   0.00975  -0.0307   0.5533   1.0000
   1.500   0.4263   0.02001   0.00970  -0.0288   0.5163   1.0000
   1.750   0.4462   0.02037   0.00974  -0.0271   0.4822   1.0000
   2.000   0.4666   0.02080   0.00984  -0.0256   0.4512   1.0000
   2.250   0.4877   0.02126   0.01003  -0.0242   0.4225   1.0000
   2.500   0.5091   0.02176   0.01025  -0.0230   0.3964   1.0000
   2.750   0.5309   0.02228   0.01055  -0.0219   0.3717   1.0000
   3.000   0.5530   0.02283   0.01088  -0.0209   0.3496   1.0000
   3.250   0.5754   0.02340   0.01124  -0.0199   0.3293   1.0000
   3.500   0.5983   0.02400   0.01166  -0.0191   0.3111   1.0000
   3.750   0.6216   0.02461   0.01212  -0.0183   0.2946   1.0000
   4.000   0.6449   0.02524   0.01262  -0.0176   0.2797   1.0000
   4.250   0.6684   0.02590   0.01311  -0.0169   0.2672   1.0000
   4.500   0.6920   0.02656   0.01365  -0.0162   0.2555   1.0000
   4.750   0.7159   0.02726   0.01432  -0.0156   0.2447   1.0000
   5.000   0.7395   0.02796   0.01482  -0.0150   0.2363   1.0000
   5.250   0.7636   0.02875   0.01566  -0.0145   0.2272   1.0000
   5.500   0.7872   0.02949   0.01625  -0.0139   0.2203   1.0000
   5.750   0.8108   0.03038   0.01719  -0.0134   0.2128   1.0000
   6.000   0.8343   0.03121   0.01797  -0.0128   0.2067   1.0000
   6.250   0.8582   0.03213   0.01878  -0.0124   0.2019   1.0000
   6.500   0.8808   0.03322   0.02003  -0.0118   0.1962   1.0000
   6.750   0.9034   0.03418   0.02098  -0.0112   0.1913   1.0000
   7.000   0.9272   0.03510   0.02174  -0.0108   0.1874   1.0000
   7.250   0.9473   0.03647   0.02335  -0.0101   0.1829   1.0000
   7.500   0.9679   0.03783   0.02485  -0.0095   0.1791   1.0000
   7.750   0.9888   0.03909   0.02616  -0.0089   0.1759   1.0000
   8.000   1.0108   0.04024   0.02726  -0.0084   0.1731   1.0000
   8.250   1.0300   0.04176   0.02887  -0.0078   0.1702   1.0000
   8.500   1.0429   0.04374   0.03118  -0.0067   0.1669   1.0000
   8.750   1.0564   0.04561   0.03326  -0.0058   0.1639   1.0000
   9.000   1.0706   0.04740   0.03518  -0.0049   0.1615   1.0000
   9.250   1.0853   0.04919   0.03710  -0.0041   0.1595   1.0000
   9.500   1.1011   0.05093   0.03888  -0.0033   0.1579   1.0000
   9.750   1.1161   0.05283   0.04081  -0.0026   0.1563   1.0000
  10.000   1.1054   0.05654   0.04497  -0.0007   0.1547   1.0000
  10.250   1.0849   0.06085   0.04969   0.0012   0.1533   1.0000
  10.500   1.0454   0.06646   0.05564   0.0028   0.1523   1.0000
  10.750   0.8534   0.09912   0.08901  -0.0156   0.1508   1.0000
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