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SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=50,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)
Reynolds number: 50,000
Max Cl/Cd: 24.47 at α=2.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1094r8-il-50000.txt
Download as CSV file: xf-sc1094r8-il-50000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.4961   0.11431   0.10738   0.0115   1.0000   0.2185
  -8.500  -0.4836   0.10986   0.10297   0.0119   1.0000   0.2257
  -8.250  -0.4950   0.10823   0.10145   0.0095   1.0000   0.2366
  -8.000  -0.4719   0.10328   0.09651   0.0115   1.0000   0.2469
  -7.750  -0.4836   0.10082   0.09418   0.0093   1.0000   0.2576
  -7.500  -0.4849   0.09847   0.09190   0.0088   1.0000   0.2725
  -7.250  -0.4663   0.09437   0.08782   0.0107   1.0000   0.2886
  -7.000  -0.4584   0.09110   0.08462   0.0116   1.0000   0.3059
  -6.750  -0.4591   0.08848   0.08210   0.0122   1.0000   0.3260
  -6.500  -0.4676   0.08611   0.07986   0.0119   1.0000   0.3478
  -6.250  -0.4419   0.08282   0.07658   0.0167   1.0000   0.3817
  -6.000  -0.4313   0.08029   0.07413   0.0201   1.0000   0.4196
  -5.750  -0.3977   0.07669   0.07053   0.0244   1.0000   0.4685
  -5.500  -0.3742   0.07386   0.06774   0.0285   1.0000   0.5236
  -5.250  -0.3628   0.07233   0.06628   0.0338   1.0000   0.5896
  -5.000  -0.3007   0.06753   0.06143   0.0361   1.0000   0.6800
  -4.750  -0.2359   0.06266   0.05651   0.0359   1.0000   0.7940
  -4.000  -0.3482   0.04429   0.03693  -0.0190   1.0000   0.2336
  -3.750  -0.3119   0.03995   0.03141  -0.0216   1.0000   0.1707
  -3.500  -0.2871   0.03727   0.02820  -0.0210   1.0000   0.1570
  -3.250  -0.2653   0.03483   0.02562  -0.0202   1.0000   0.1540
  -3.000  -0.2418   0.03272   0.02320  -0.0194   1.0000   0.1503
  -2.750  -0.2161   0.03099   0.02093  -0.0185   1.0000   0.1454
  -2.500  -0.1914   0.02950   0.01910  -0.0175   1.0000   0.1440
  -2.250  -0.1678   0.02788   0.01744  -0.0167   1.0000   0.1468
  -2.000  -0.1438   0.02663   0.01612  -0.0158   1.0000   0.1513
  -1.750  -0.1187   0.02556   0.01489  -0.0148   1.0000   0.1552
  -1.500  -0.0938   0.02447   0.01384  -0.0139   1.0000   0.1627
  -1.250  -0.0691   0.02364   0.01298  -0.0129   1.0000   0.1738
  -1.000  -0.0442   0.02278   0.01221  -0.0122   1.0000   0.1905
  -0.750  -0.0196   0.02185   0.01148  -0.0116   1.0000   0.2218
  -0.500   0.0099   0.01806   0.01065  -0.0087   1.0000   1.0000
  -0.250   0.0283   0.01840   0.01048  -0.0076   1.0000   1.0000
   0.000   0.0461   0.01881   0.01063  -0.0069   1.0000   1.0000
   0.250   0.0635   0.01933   0.01097  -0.0065   1.0000   1.0000
   0.500   0.0803   0.01998   0.01150  -0.0064   1.0000   1.0000
   0.750   0.1468   0.02095   0.01230  -0.0153   0.9773   1.0000
   1.000   0.2534   0.02129   0.01256  -0.0293   0.9279   1.0000
   1.250   0.3429   0.02067   0.01196  -0.0380   0.8780   1.0000
   1.500   0.3923   0.01996   0.01121  -0.0385   0.8260   1.0000
   1.750   0.4209   0.01948   0.01059  -0.0352   0.7688   1.0000
   2.000   0.4428   0.01923   0.01006  -0.0310   0.7074   1.0000
   2.250   0.4624   0.01936   0.00979  -0.0271   0.6404   1.0000
   2.500   0.4823   0.01983   0.00976  -0.0239   0.5746   1.0000
   2.750   0.5039   0.02059   0.01003  -0.0215   0.5146   1.0000
   3.000   0.5269   0.02154   0.01054  -0.0199   0.4647   1.0000
   3.250   0.5506   0.02255   0.01121  -0.0187   0.4245   1.0000
   3.500   0.5752   0.02359   0.01196  -0.0177   0.3934   1.0000
   3.750   0.6001   0.02469   0.01287  -0.0169   0.3683   1.0000
   4.000   0.6253   0.02583   0.01391  -0.0163   0.3476   1.0000
   4.250   0.6506   0.02700   0.01493  -0.0158   0.3308   1.0000
   4.500   0.6758   0.02822   0.01616  -0.0153   0.3160   1.0000
   4.750   0.7004   0.02963   0.01769  -0.0149   0.3034   1.0000
   5.000   0.7257   0.03099   0.01888  -0.0144   0.2935   1.0000
   5.250   0.7490   0.03269   0.02092  -0.0141   0.2842   1.0000
   5.500   0.7739   0.03412   0.02222  -0.0137   0.2764   1.0000
   5.750   0.7947   0.03625   0.02475  -0.0134   0.2694   1.0000
   6.000   0.8161   0.03833   0.02704  -0.0131   0.2637   1.0000
   6.250   0.8397   0.04009   0.02877  -0.0127   0.2588   1.0000
   6.500   0.8573   0.04284   0.03182  -0.0124   0.2547   1.0000
   6.750   0.8703   0.04618   0.03561  -0.0124   0.2512   1.0000
   7.000   0.8809   0.05002   0.03985  -0.0125   0.2496   1.0000
   7.250   0.8859   0.05463   0.04483  -0.0129   0.2491   1.0000
   7.500   0.8834   0.06022   0.05076  -0.0140   0.2498   1.0000
   7.750   0.8742   0.06669   0.05748  -0.0158   0.2520   1.0000
   8.000   0.8686   0.07281   0.06373  -0.0176   0.2546   1.0000
   8.250   0.8781   0.07754   0.06852  -0.0184   0.2574   1.0000
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