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

SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)
Reynolds number: 200,000
Max Cl/Cd: 45.59 at α=5.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-sc1094r8-il-200000.txt
Download as CSV file: xf-sc1094r8-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.000  -0.5069   0.10383   0.10023   0.0067   1.0000   0.0468
  -8.750  -0.5062   0.09965   0.09608   0.0035   1.0000   0.0485
  -8.500  -0.5202   0.09291   0.08940  -0.0064   1.0000   0.0493
  -8.250  -0.5049   0.09096   0.08747  -0.0026   1.0000   0.0500
  -8.000  -0.4991   0.08767   0.08420  -0.0038   1.0000   0.0509
  -7.750  -0.4980   0.08357   0.08014  -0.0072   1.0000   0.0519
  -7.500  -0.4993   0.07767   0.07422  -0.0151   1.0000   0.0533
  -7.250  -0.5001   0.07078   0.06719  -0.0226   1.0000   0.0544
  -7.000  -0.4881   0.06816   0.06461  -0.0220   1.0000   0.0551
  -6.750  -0.4771   0.06486   0.06127  -0.0231   1.0000   0.0565
  -6.500  -0.4709   0.05870   0.05477  -0.0278   1.0000   0.0596
  -6.250  -0.4565   0.05619   0.05232  -0.0272   1.0000   0.0604
  -6.000  -0.4435   0.05267   0.04851  -0.0282   1.0000   0.0646
  -5.750  -0.4314   0.04932   0.04511  -0.0278   1.0000   0.0657
  -5.500  -0.4191   0.04707   0.04244  -0.0269   1.0000   0.0709
  -5.250  -0.4064   0.04397   0.03945  -0.0258   1.0000   0.0717
  -5.000  -0.3930   0.04260   0.03767  -0.0242   1.0000   0.0775
  -4.750  -0.3803   0.03953   0.03473  -0.0230   1.0000   0.0785
  -4.500  -0.3666   0.03773   0.03298  -0.0214   1.0000   0.0804
  -4.250  -0.3524   0.03574   0.03079  -0.0200   1.0000   0.0865
  -4.000  -0.3370   0.03417   0.02899  -0.0186   1.0000   0.0937
  -3.750  -0.3212   0.03250   0.02739  -0.0173   1.0000   0.0966
  -3.500  -0.3023   0.03080   0.02552  -0.0165   0.9997   0.1039
  -3.250  -0.2510   0.02261   0.01566  -0.0168   0.9965   0.0536
  -3.000  -0.2072   0.02008   0.01281  -0.0194   0.9920   0.0503
  -2.750  -0.1630   0.01840   0.01071  -0.0218   0.9878   0.0494
  -2.500  -0.1227   0.01739   0.00980  -0.0243   0.9812   0.0519
  -2.250  -0.0778   0.01637   0.00859  -0.0271   0.9759   0.0539
  -2.000  -0.0312   0.01527   0.00760  -0.0307   0.9722   0.0562
  -1.750   0.0080   0.01447   0.00683  -0.0325   0.9626   0.0599
  -1.500   0.0505   0.01369   0.00617  -0.0349   0.9513   0.0662
  -1.250   0.0846   0.01297   0.00555  -0.0354   0.9344   0.0730
  -1.000   0.1126   0.01240   0.00506  -0.0346   0.9161   0.0853
  -0.750   0.1377   0.01168   0.00456  -0.0333   0.8973   0.1223
  -0.500   0.1399   0.00892   0.00456  -0.0270   0.8792   0.8469
  -0.250   0.1653   0.00887   0.00455  -0.0238   0.8567   0.9616
   0.000   0.2343   0.00880   0.00426  -0.0309   0.8262   1.0000
   0.250   0.2560   0.00875   0.00403  -0.0291   0.7918   1.0000
   0.500   0.2781   0.00877   0.00381  -0.0274   0.7516   1.0000
   0.750   0.3005   0.00885   0.00363  -0.0258   0.7034   1.0000
   1.000   0.3231   0.00904   0.00348  -0.0244   0.6453   1.0000
   1.250   0.3458   0.00932   0.00340  -0.0231   0.5809   1.0000
   1.500   0.3687   0.00969   0.00339  -0.0220   0.5173   1.0000
   1.750   0.3920   0.01008   0.00343  -0.0210   0.4612   1.0000
   2.000   0.4159   0.01049   0.00352  -0.0203   0.4126   1.0000
   2.250   0.4404   0.01089   0.00364  -0.0197   0.3701   1.0000
   2.500   0.4652   0.01130   0.00380  -0.0192   0.3305   1.0000
   2.750   0.4903   0.01174   0.00398  -0.0187   0.2939   1.0000
   3.000   0.5158   0.01216   0.00420  -0.0183   0.2623   1.0000
   3.250   0.5412   0.01263   0.00444  -0.0179   0.2383   1.0000
   3.500   0.5671   0.01306   0.00472  -0.0176   0.2196   1.0000
   3.750   0.5928   0.01354   0.00504  -0.0172   0.2050   1.0000
   4.000   0.6191   0.01393   0.00537  -0.0169   0.1935   1.0000
   4.250   0.6449   0.01445   0.00577  -0.0166   0.1841   1.0000
   4.500   0.6710   0.01490   0.00614  -0.0163   0.1759   1.0000
   4.750   0.6969   0.01546   0.00663  -0.0160   0.1690   1.0000
   5.000   0.7232   0.01591   0.00704  -0.0157   0.1630   1.0000
   5.250   0.7486   0.01667   0.00765  -0.0154   0.1579   1.0000
   5.500   0.7752   0.01709   0.00814  -0.0151   0.1534   1.0000
   5.750   0.8014   0.01758   0.00860  -0.0148   0.1491   1.0000
   6.000   0.8271   0.01836   0.00925  -0.0146   0.1452   1.0000
   6.250   0.8533   0.01895   0.00991  -0.0143   0.1421   1.0000
   6.500   0.8795   0.01952   0.01055  -0.0140   0.1390   1.0000
   6.750   0.9056   0.02013   0.01115  -0.0138   0.1362   1.0000
   7.000   0.9314   0.02085   0.01181  -0.0136   0.1336   1.0000
   7.250   0.9570   0.02187   0.01284  -0.0134   0.1312   1.0000
   7.500   0.9825   0.02251   0.01363  -0.0130   0.1289   1.0000
   7.750   1.0078   0.02327   0.01449  -0.0127   0.1268   1.0000
   8.000   1.0331   0.02407   0.01535  -0.0124   0.1249   1.0000
   8.250   1.0582   0.02490   0.01622  -0.0122   0.1231   1.0000
   8.500   1.0834   0.02590   0.01720  -0.0120   0.1215   1.0000
   8.750   1.1073   0.02737   0.01873  -0.0118   0.1198   1.0000
   9.000   1.1301   0.02832   0.01994  -0.0112   0.1183   1.0000
   9.250   1.1524   0.02951   0.02135  -0.0106   0.1169   1.0000
   9.500   1.1744   0.03080   0.02282  -0.0101   0.1155   1.0000
   9.750   1.1960   0.03212   0.02431  -0.0096   0.1143   1.0000
  10.000   1.2178   0.03338   0.02568  -0.0091   0.1131   1.0000
  10.250   1.2393   0.03458   0.02697  -0.0086   0.1118   1.0000
  10.500   1.2607   0.03596   0.02840  -0.0083   0.1106   1.0000
  10.750   1.2793   0.03849   0.03102  -0.0079   0.1096   1.0000
  11.000   1.2911   0.04057   0.03349  -0.0066   0.1089   1.0000
  11.250   1.2992   0.04314   0.03645  -0.0052   0.1081   1.0000
  11.500   1.3021   0.04616   0.03988  -0.0035   0.1073   1.0000
  11.750   1.2989   0.04959   0.04369  -0.0017   0.1064   1.0000
  12.000   1.2880   0.05359   0.04806   0.0002   0.1057   1.0000
  12.250   1.2604   0.05855   0.05337   0.0026   0.1056   1.0000
  12.500   1.2035   0.06585   0.06102   0.0037   0.1060   1.0000
  12.750   1.0320   0.09819   0.09379  -0.0173   0.1101   1.0000
  13.000   1.0423   0.10011   0.09571  -0.0162   0.1096   1.0000
<< Back to SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)

Polar data table (+)

Polar graphs


<< Back to SIKORSKY SC1094 R8 AIRFOIL (sc1094r8-il)