Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

SIKORSKY SC1095 AIRFOIL (sc1095-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1095 AIRFOIL (sc1095-il)
Reynolds number: 1,000,000
Max Cl/Cd: 86.95 at α=9.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1095-il-1000000.txt
Download as CSV file: xf-sc1095-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SIKORSKY SC1095 AIRFOIL                         
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -15.000  -1.0592   0.09552   0.09313   0.0115   1.0000   0.0051
 -14.750  -1.0997   0.08387   0.08138   0.0050   1.0000   0.0050
 -14.500  -1.1398   0.07172   0.06911  -0.0020   1.0000   0.0050
 -14.250  -1.1697   0.05929   0.05650  -0.0106   1.0000   0.0049
 -14.000  -1.1881   0.04848   0.04546  -0.0210   1.0000   0.0048
 -13.750  -1.2047   0.04178   0.03854  -0.0265   1.0000   0.0048
 -13.500  -1.2174   0.03755   0.03413  -0.0280   1.0000   0.0048
 -13.250  -1.2274   0.03457   0.03098  -0.0268   1.0000   0.0049
 -13.000  -1.2316   0.03203   0.02825  -0.0249   1.0000   0.0049
 -12.750  -1.2277   0.02970   0.02573  -0.0235   1.0000   0.0049
 -12.500  -1.2184   0.02772   0.02359  -0.0224   1.0000   0.0050
 -12.250  -1.2056   0.02599   0.02169  -0.0214   1.0000   0.0051
 -12.000  -1.1901   0.02447   0.02002  -0.0205   1.0000   0.0051
 -11.750  -1.1723   0.02312   0.01855  -0.0198   1.0000   0.0052
 -11.500  -1.1530   0.02192   0.01722  -0.0191   1.0000   0.0053
 -11.250  -1.1323   0.02084   0.01603  -0.0185   1.0000   0.0054
 -11.000  -1.1106   0.01985   0.01493  -0.0180   1.0000   0.0055
 -10.750  -1.0881   0.01894   0.01392  -0.0176   1.0000   0.0055
 -10.500  -1.0649   0.01809   0.01297  -0.0172   1.0000   0.0056
 -10.250  -1.0410   0.01730   0.01209  -0.0168   1.0000   0.0057
 -10.000  -1.0167   0.01657   0.01127  -0.0165   1.0000   0.0058
  -9.750  -0.9918   0.01589   0.01051  -0.0162   1.0000   0.0059
  -9.500  -0.9665   0.01525   0.00979  -0.0159   1.0000   0.0061
  -9.250  -0.9409   0.01466   0.00912  -0.0157   1.0000   0.0062
  -9.000  -0.9149   0.01411   0.00851  -0.0155   1.0000   0.0064
  -8.750  -0.8886   0.01361   0.00795  -0.0153   1.0000   0.0066
  -8.500  -0.8622   0.01309   0.00737  -0.0152   1.0000   0.0069
  -8.250  -0.8357   0.01257   0.00680  -0.0150   1.0000   0.0075
  -8.000  -0.8090   0.01210   0.00629  -0.0148   1.0000   0.0083
  -7.750  -0.7827   0.01152   0.00572  -0.0147   1.0000   0.0125
  -7.500  -0.7563   0.01097   0.00527  -0.0146   1.0000   0.0239
  -7.250  -0.7292   0.01063   0.00496  -0.0145   1.0000   0.0286
  -7.000  -0.7016   0.01040   0.00472  -0.0145   1.0000   0.0312
  -6.750  -0.6746   0.01006   0.00440  -0.0144   1.0000   0.0348
  -6.500  -0.6478   0.00980   0.00414  -0.0142   1.0000   0.0379
  -6.250  -0.6217   0.00951   0.00388  -0.0139   1.0000   0.0430
  -6.000  -0.5969   0.00924   0.00366  -0.0133   1.0000   0.0502
  -5.750  -0.5731   0.00904   0.00349  -0.0125   1.0000   0.0580
  -5.500  -0.5459   0.00883   0.00334  -0.0125   0.9992   0.0665
  -5.250  -0.5111   0.00866   0.00318  -0.0140   0.9969   0.0726
  -5.000  -0.4757   0.00849   0.00305  -0.0156   0.9950   0.0788
  -4.750  -0.4404   0.00837   0.00293  -0.0172   0.9925   0.0832
  -4.500  -0.4069   0.00819   0.00280  -0.0184   0.9878   0.0899
  -4.250  -0.3722   0.00808   0.00269  -0.0197   0.9819   0.0938
  -4.000  -0.3442   0.00802   0.00259  -0.0195   0.9707   0.0963
  -3.750  -0.3208   0.00788   0.00245  -0.0182   0.9579   0.1012
  -3.500  -0.2950   0.00774   0.00233  -0.0175   0.9477   0.1055
  -3.250  -0.2686   0.00765   0.00221  -0.0170   0.9383   0.1088
  -3.000  -0.2427   0.00750   0.00207  -0.0163   0.9289   0.1152
  -2.750  -0.2160   0.00737   0.00195  -0.0159   0.9183   0.1219
  -2.500  -0.1889   0.00722   0.00183  -0.0155   0.9072   0.1334
  -2.250  -0.1618   0.00706   0.00171  -0.0152   0.8961   0.1502
  -2.000  -0.1347   0.00686   0.00160  -0.0149   0.8840   0.1810
  -1.750  -0.1074   0.00663   0.00149  -0.0147   0.8694   0.2272
  -1.500  -0.0802   0.00637   0.00139  -0.0145   0.8501   0.2845
  -1.250  -0.0530   0.00612   0.00130  -0.0143   0.8268   0.3521
  -1.000  -0.0255   0.00582   0.00121  -0.0143   0.8038   0.4351
  -0.750   0.0019   0.00549   0.00115  -0.0143   0.7800   0.5360
  -0.500   0.0296   0.00524   0.00111  -0.0142   0.7528   0.6270
  -0.250   0.0573   0.00511   0.00110  -0.0140   0.7228   0.6934
   0.000   0.0850   0.00508   0.00110  -0.0138   0.6848   0.7436
   0.250   0.1126   0.00514   0.00112  -0.0136   0.6397   0.7820
   0.500   0.1400   0.00526   0.00115  -0.0134   0.5862   0.8141
   0.750   0.1669   0.00543   0.00120  -0.0131   0.5284   0.8446
   1.000   0.1937   0.00564   0.00127  -0.0127   0.4729   0.8699
   1.250   0.2202   0.00584   0.00134  -0.0123   0.4237   0.8896
   1.500   0.2454   0.00600   0.00143  -0.0115   0.3864   0.9145
   1.750   0.2689   0.00616   0.00151  -0.0103   0.3553   0.9369
   2.000   0.2929   0.00632   0.00158  -0.0092   0.3283   0.9548
   2.250   0.3166   0.00645   0.00163  -0.0081   0.3024   0.9718
   2.500   0.3472   0.00660   0.00167  -0.0085   0.2745   0.9847
   3.000   0.4196   0.00705   0.00186  -0.0122   0.2152   0.9973
   3.250   0.4533   0.00731   0.00198  -0.0135   0.1872   1.0000
   3.500   0.4779   0.00750   0.00208  -0.0129   0.1696   1.0000
   3.750   0.5040   0.00770   0.00221  -0.0126   0.1550   1.0000
   4.000   0.5311   0.00791   0.00235  -0.0125   0.1427   1.0000
   4.250   0.5588   0.00809   0.00248  -0.0125   0.1333   1.0000
   4.500   0.5867   0.00827   0.00264  -0.0125   0.1251   1.0000
   4.750   0.6146   0.00850   0.00281  -0.0126   0.1162   1.0000
   5.000   0.6428   0.00867   0.00297  -0.0127   0.1110   1.0000
   5.250   0.6707   0.00891   0.00316  -0.0127   0.1044   1.0000
   5.500   0.6988   0.00911   0.00337  -0.0128   0.0998   1.0000
   5.750   0.7268   0.00931   0.00355  -0.0128   0.0957   1.0000
   6.000   0.7546   0.00957   0.00378  -0.0129   0.0909   1.0000
   6.250   0.7823   0.00983   0.00405  -0.0129   0.0875   1.0000
   6.500   0.8103   0.00999   0.00423  -0.0129   0.0849   1.0000
   6.750   0.8380   0.01021   0.00444  -0.0130   0.0813   1.0000
   7.000   0.8653   0.01053   0.00474  -0.0129   0.0774   1.0000
   7.250   0.8926   0.01081   0.00505  -0.0129   0.0751   1.0000
   7.500   0.9204   0.01097   0.00524  -0.0129   0.0733   1.0000
   7.750   0.9480   0.01117   0.00544  -0.0129   0.0702   1.0000
   8.000   0.9750   0.01147   0.00571  -0.0129   0.0662   1.0000
   8.250   1.0019   0.01175   0.00602  -0.0128   0.0633   1.0000
   8.500   1.0294   0.01192   0.00621  -0.0128   0.0610   1.0000
   8.750   1.0563   0.01218   0.00646  -0.0128   0.0577   1.0000
   9.000   1.0826   0.01253   0.00680  -0.0127   0.0530   1.0000
   9.250   1.1095   0.01276   0.00705  -0.0126   0.0493   1.0000
   9.500   1.1349   0.01322   0.00743  -0.0124   0.0387   1.0000
   9.750   1.1540   0.01473   0.00870  -0.0116   0.0127   1.0000
  10.000   1.1776   0.01547   0.00948  -0.0111   0.0100   1.0000
  10.250   1.2015   0.01612   0.01019  -0.0107   0.0090   1.0000
  10.500   1.2241   0.01694   0.01109  -0.0101   0.0081   1.0000
  10.750   1.2475   0.01759   0.01182  -0.0096   0.0078   1.0000
  11.000   1.2705   0.01825   0.01256  -0.0091   0.0074   1.0000
  11.250   1.2929   0.01897   0.01335  -0.0086   0.0071   1.0000
  11.500   1.3144   0.01974   0.01420  -0.0079   0.0067   1.0000
  11.750   1.3347   0.02064   0.01518  -0.0072   0.0064   1.0000
  12.000   1.3528   0.02175   0.01640  -0.0062   0.0062   1.0000
  12.250   1.3673   0.02319   0.01799  -0.0049   0.0059   1.0000
  12.500   1.3815   0.02452   0.01945  -0.0036   0.0058   1.0000
  12.750   1.3971   0.02559   0.02062  -0.0025   0.0058   1.0000
  13.000   1.4107   0.02676   0.02190  -0.0012   0.0057   1.0000
  13.250   1.4215   0.02804   0.02330   0.0004   0.0056   1.0000
  13.500   1.4266   0.02942   0.02480   0.0027   0.0056   1.0000
  13.750   1.4280   0.03105   0.02654   0.0049   0.0055   1.0000
  14.000   1.4277   0.03301   0.02863   0.0066   0.0054   1.0000
  14.250   1.4252   0.03544   0.03119   0.0075   0.0054   1.0000
  14.500   1.4204   0.03847   0.03437   0.0076   0.0054   1.0000
  14.750   1.4129   0.04233   0.03837   0.0065   0.0053   1.0000
  15.000   1.4011   0.04747   0.04368   0.0039   0.0053   1.0000
  15.250   1.3833   0.05460   0.05099  -0.0009   0.0053   1.0000
  15.500   1.3564   0.06430   0.06090  -0.0075   0.0053   1.0000
  15.750   1.3188   0.07597   0.07278  -0.0145   0.0054   1.0000
  16.000   1.2745   0.08823   0.08522  -0.0210   0.0055   1.0000
<< Back to SIKORSKY SC1095 AIRFOIL (sc1095-il)

Polar data table (+)

Polar graphs


<< Back to SIKORSKY SC1095 AIRFOIL (sc1095-il)