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

SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il)
Reynolds number: 100,000
Max Cl/Cd: 33.99 at α=5.25°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1012r8-il-100000.txt
Download as CSV file: xf-sc1012r8-il-100000.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 =     0.100 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.2900   0.10059   0.09591  -0.0161   1.0000   0.1065
  -8.750  -0.3100   0.09731   0.09268  -0.0205   1.0000   0.1098
  -8.500  -0.3463   0.09352   0.08896  -0.0276   1.0000   0.1106
  -8.250  -0.3063   0.08877   0.08426  -0.0217   1.0000   0.1129
  -8.000  -0.2913   0.08569   0.08121  -0.0202   1.0000   0.1157
  -7.750  -0.4427   0.08821   0.08340  -0.0285   1.0000   0.1114
  -7.500  -0.4087   0.08504   0.08038  -0.0222   1.0000   0.1136
  -7.250  -0.3978   0.08230   0.07769  -0.0210   1.0000   0.1164
  -7.000  -0.3979   0.07897   0.07440  -0.0226   1.0000   0.1199
  -6.750  -0.4387   0.07711   0.07222  -0.0282   1.0000   0.1258
  -6.500  -0.4348   0.07211   0.06736  -0.0268   1.0000   0.1275
  -6.250  -0.4224   0.06907   0.06449  -0.0240   1.0000   0.1295
  -6.000  -0.4182   0.06685   0.06234  -0.0216   1.0000   0.1325
  -5.750  -0.4200   0.06467   0.06014  -0.0200   1.0000   0.1372
  -5.500  -0.4328   0.06207   0.05723  -0.0199   1.0000   0.1448
  -5.250  -0.4246   0.05924   0.05456  -0.0174   1.0000   0.1473
  -5.000  -0.4183   0.05719   0.05256  -0.0153   1.0000   0.1520
  -4.750  -0.4171   0.05484   0.04995  -0.0150   1.0000   0.1638
  -4.500  -0.4076   0.05256   0.04782  -0.0128   1.0000   0.1687
  -4.250  -0.4007   0.05046   0.04555  -0.0122   1.0000   0.1833
  -4.000  -0.3897   0.04854   0.04372  -0.0105   1.0000   0.1915
  -3.750  -0.3796   0.04636   0.04151  -0.0096   1.0000   0.2066
  -3.500  -0.3477   0.04390   0.03902  -0.0122   0.9949   0.2303
  -3.250  -0.2707   0.03582   0.02876  -0.0195   0.9878   0.1120
  -3.000  -0.2199   0.03158   0.02406  -0.0230   0.9808   0.0929
  -2.750  -0.1682   0.02918   0.02127  -0.0271   0.9729   0.0916
  -2.500  -0.1189   0.02711   0.01884  -0.0304   0.9632   0.0903
  -2.250  -0.0705   0.02542   0.01690  -0.0335   0.9527   0.0906
  -2.000  -0.0215   0.02419   0.01551  -0.0367   0.9413   0.0951
  -1.750   0.0294   0.02266   0.01400  -0.0402   0.9310   0.1003
  -1.500   0.0831   0.02143   0.01281  -0.0439   0.9207   0.1093
  -1.250   0.1242   0.02012   0.01172  -0.0452   0.9048   0.1223
  -1.000   0.1602   0.01884   0.01060  -0.0450   0.8864   0.1443
  -0.750   0.1868   0.01731   0.00949  -0.0433   0.8650   0.2100
  -0.500   0.2942   0.01486   0.00940  -0.0503   0.8458   1.0000
  -0.250   0.3124   0.01455   0.00890  -0.0474   0.8148   1.0000
   0.000   0.3308   0.01429   0.00845  -0.0446   0.7808   1.0000
   0.250   0.3496   0.01409   0.00802  -0.0420   0.7429   1.0000
   0.500   0.3691   0.01398   0.00763  -0.0395   0.7009   1.0000
   0.750   0.3890   0.01399   0.00733  -0.0373   0.6537   1.0000
   1.000   0.4093   0.01413   0.00710  -0.0353   0.6060   1.0000
   1.250   0.4299   0.01438   0.00700  -0.0335   0.5596   1.0000
   1.500   0.4505   0.01472   0.00698  -0.0319   0.5175   1.0000
   1.750   0.4713   0.01512   0.00704  -0.0304   0.4797   1.0000
   2.000   0.4922   0.01555   0.00716  -0.0290   0.4451   1.0000
   2.250   0.5131   0.01604   0.00733  -0.0276   0.4134   1.0000
   2.500   0.5341   0.01655   0.00756  -0.0263   0.3837   1.0000
   2.750   0.5556   0.01711   0.00785  -0.0251   0.3567   1.0000
   3.000   0.5776   0.01766   0.00819  -0.0240   0.3326   1.0000
   3.250   0.6002   0.01824   0.00855  -0.0230   0.3123   1.0000
   3.500   0.6235   0.01883   0.00896  -0.0221   0.2949   1.0000
   3.750   0.6473   0.01943   0.00941  -0.0214   0.2799   1.0000
   4.000   0.6715   0.02008   0.00987  -0.0207   0.2676   1.0000
   4.250   0.6961   0.02066   0.01034  -0.0201   0.2563   1.0000
   4.500   0.7210   0.02134   0.01097  -0.0195   0.2462   1.0000
   4.750   0.7461   0.02200   0.01144  -0.0191   0.2376   1.0000
   5.000   0.7710   0.02272   0.01221  -0.0186   0.2292   1.0000
   5.250   0.7965   0.02343   0.01278  -0.0182   0.2224   1.0000
   5.500   0.8219   0.02437   0.01368  -0.0178   0.2166   1.0000
   5.750   0.8467   0.02515   0.01453  -0.0173   0.2104   1.0000
   6.000   0.8724   0.02596   0.01519  -0.0171   0.2052   1.0000
   6.250   0.8971   0.02705   0.01633  -0.0167   0.2005   1.0000
   6.500   0.9209   0.02802   0.01745  -0.0161   0.1959   1.0000
   6.750   0.9454   0.02901   0.01846  -0.0157   0.1921   1.0000
   7.000   0.9708   0.03012   0.01949  -0.0156   0.1888   1.0000
   7.250   0.9937   0.03162   0.02108  -0.0151   0.1858   1.0000
   7.500   1.0141   0.03296   0.02270  -0.0143   0.1825   1.0000
   7.750   1.0352   0.03429   0.02419  -0.0136   0.1793   1.0000
   8.000   1.0573   0.03556   0.02555  -0.0131   0.1765   1.0000
   8.250   1.0793   0.03696   0.02700  -0.0127   0.1743   1.0000
   8.500   1.1012   0.03877   0.02880  -0.0124   0.1724   1.0000
   8.750   1.1167   0.04117   0.03145  -0.0115   0.1709   1.0000
   9.000   1.1263   0.04362   0.03431  -0.0100   0.1695   1.0000
   9.250   1.1321   0.04647   0.03755  -0.0085   0.1681   1.0000
   9.500   1.1333   0.04972   0.04117  -0.0068   0.1667   1.0000
   9.750   1.1279   0.05348   0.04528  -0.0050   0.1656   1.0000
  10.000   1.1101   0.05825   0.05041  -0.0030   0.1652   1.0000
  10.250   1.0588   0.06543   0.05799  -0.0006   0.1660   1.0000
  10.500   0.9486   0.08218   0.07512  -0.0061   0.1698   1.0000
  10.750   0.9286   0.09104   0.08406  -0.0098   0.1721   1.0000
<< Back to SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il)

Polar data table (+)

Polar graphs


<< Back to SIKORSKY SC1012R8 AIRFOIL (sc1012r8-il)