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SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=100,000 Ncrit=9


Details Polar file
Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)
Reynolds number: 100,000
Max Cl/Cd: 28.15 at α=3.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-nasasc2-0714-il-100000.txt
Download as CSV file: xf-nasasc2-0714-il-100000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: SC(2)-0714 Supercritical airfoil (coordinates fr
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.6153   0.09243   0.08654  -0.0515   1.0000   0.1227
 -11.250  -0.6001   0.09024   0.08437  -0.0492   1.0000   0.1207
 -11.000  -0.7412   0.07131   0.06525  -0.0552   1.0000   0.1036
 -10.750  -0.8739   0.06162   0.05471  -0.0533   1.0000   0.0962
 -10.500  -0.8757   0.05818   0.05096  -0.0526   1.0000   0.0956
 -10.250  -0.8731   0.05414   0.04665  -0.0522   1.0000   0.0954
 -10.000  -0.8680   0.05030   0.04243  -0.0524   1.0000   0.0960
  -9.750  -0.8555   0.04684   0.03893  -0.0521   1.0000   0.0977
  -9.500  -0.8386   0.04502   0.03713  -0.0514   1.0000   0.0997
  -9.250  -0.8221   0.04254   0.03442  -0.0515   1.0000   0.1012
  -9.000  -0.8034   0.03999   0.03157  -0.0518   1.0000   0.1026
  -8.750  -0.7824   0.03779   0.02906  -0.0522   1.0000   0.1048
  -8.500  -0.7590   0.03594   0.02679  -0.0528   1.0000   0.1078
  -8.250  -0.7354   0.03388   0.02445  -0.0532   1.0000   0.1103
  -8.000  -0.7132   0.03228   0.02287  -0.0528   1.0000   0.1130
  -7.750  -0.6894   0.03111   0.02165  -0.0526   1.0000   0.1166
  -7.500  -0.6641   0.03005   0.02040  -0.0527   1.0000   0.1212
  -7.250  -0.6395   0.02880   0.01903  -0.0524   1.0000   0.1253
  -7.000  -0.6168   0.02777   0.01813  -0.0516   1.0000   0.1298
  -6.750  -0.5919   0.02700   0.01728  -0.0514   1.0000   0.1362
  -6.500  -0.5686   0.02607   0.01642  -0.0507   1.0000   0.1428
  -6.250  -0.5446   0.02536   0.01579  -0.0502   1.0000   0.1510
  -6.000  -0.5209   0.02458   0.01514  -0.0495   1.0000   0.1609
  -5.750  -0.4960   0.02389   0.01460  -0.0492   1.0000   0.1752
  -5.500  -0.4700   0.02319   0.01415  -0.0493   1.0000   0.1949
  -5.250  -0.4406   0.02236   0.01370  -0.0503   1.0000   0.2311
  -5.000  -0.4007   0.02069   0.01398  -0.0541   1.0000   0.4602
  -4.750  -0.3972   0.02241   0.01607  -0.0467   1.0000   0.5660
  -4.500  -0.3818   0.02386   0.01744  -0.0428   1.0000   0.6025
  -4.250  -0.3712   0.02529   0.01883  -0.0376   1.0000   0.6218
  -4.000  -0.3604   0.02658   0.02008  -0.0327   1.0000   0.6382
  -3.750  -0.3485   0.02772   0.02118  -0.0282   1.0000   0.6537
  -3.500  -0.3349   0.02869   0.02212  -0.0243   1.0000   0.6691
  -3.250  -0.3296   0.02964   0.02307  -0.0180   1.0000   0.6790
  -3.000  -0.3177   0.03031   0.02371  -0.0139   1.0000   0.6915
  -2.750  -0.3011   0.03081   0.02417  -0.0113   1.0000   0.7055
  -2.500  -0.2857   0.03126   0.02459  -0.0085   1.0000   0.7184
  -2.250  -0.2769   0.03153   0.02486  -0.0039   1.0000   0.7279
  -2.000  -0.2627   0.03182   0.02514  -0.0010   1.0000   0.7419
  -1.750  -0.2535   0.03215   0.02547   0.0034   1.0000   0.7585
  -1.500  -0.2471   0.03234   0.02568   0.0085   1.0000   0.7762
  -1.250  -0.2403   0.03237   0.02573   0.0132   1.0000   0.7943
  -1.000  -0.2292   0.03226   0.02562   0.0165   1.0000   0.8101
  -0.750  -0.2097   0.03218   0.02552   0.0172   1.0000   0.8218
  -0.500  -0.1916   0.03201   0.02535   0.0181   1.0000   0.8302
  -0.250  -0.1656   0.03205   0.02537   0.0167   1.0000   0.8363
   0.000  -0.1224   0.03224   0.02554   0.0129   0.9915   0.8414
   0.250  -0.0746   0.03263   0.02592   0.0077   0.9824   0.8464
   0.500  -0.0294   0.03283   0.02611   0.0032   0.9712   0.8508
   0.750   0.0098   0.03275   0.02606   0.0005   0.9584   0.8559
   1.000   0.0560   0.03284   0.02618  -0.0038   0.9450   0.8609
   1.250   0.1069   0.03290   0.02627  -0.0090   0.9311   0.8638
   1.500   0.1531   0.03249   0.02592  -0.0125   0.9161   0.8658
   1.750   0.2046   0.03174   0.02522  -0.0163   0.8977   0.8684
   2.000   0.2611   0.03060   0.02417  -0.0203   0.8785   0.8712
   2.250   0.3109   0.02962   0.02328  -0.0235   0.8622   0.8732
   2.500   0.3605   0.02847   0.02224  -0.0264   0.8458   0.8747
   2.750   0.4150   0.02668   0.02057  -0.0292   0.8262   0.8762
   3.000   0.4713   0.02451   0.01853  -0.0316   0.8050   0.8776
   3.250   0.5004   0.02330   0.01743  -0.0304   0.7729   0.8793
   3.500   0.5342   0.02196   0.01614  -0.0296   0.7226   0.8814
   3.750   0.6018   0.02138   0.01409  -0.0332   0.4463   0.8835
   4.000   0.6081   0.02308   0.01462  -0.0300   0.2883   0.8848
   4.250   0.6256   0.02430   0.01529  -0.0288   0.2268   0.8870
   4.500   0.6498   0.02532   0.01601  -0.0288   0.1959   0.8892
   4.750   0.6783   0.02626   0.01677  -0.0295   0.1757   0.8909
   5.000   0.7106   0.02727   0.01766  -0.0309   0.1615   0.8919
   5.250   0.7443   0.02838   0.01859  -0.0326   0.1506   0.8930
   5.500   0.7735   0.02908   0.01934  -0.0330   0.1421   0.8947
   5.750   0.8066   0.03029   0.02045  -0.0344   0.1346   0.8964
   6.000   0.8377   0.03123   0.02153  -0.0353   0.1281   0.8975
   6.250   0.8725   0.03272   0.02286  -0.0372   0.1223   0.8987
   6.500   0.9018   0.03397   0.02438  -0.0378   0.1174   0.8998
   6.750   0.9319   0.03532   0.02589  -0.0386   0.1131   0.9011
   7.000   0.9623   0.03685   0.02745  -0.0397   0.1093   0.9024
   7.250   0.9902   0.03911   0.02990  -0.0405   0.1060   0.9037
   7.500   1.0126   0.04085   0.03208  -0.0400   0.1030   0.9053
   7.750   1.0344   0.04306   0.03464  -0.0396   0.1010   0.9071
   8.000   1.0524   0.04521   0.03711  -0.0385   0.0993   0.9089
   8.250   1.0725   0.04727   0.03935  -0.0381   0.0973   0.9105
   8.500   1.0969   0.04963   0.04169  -0.0387   0.0950   0.9121
   8.750   1.1085   0.05341   0.04578  -0.0376   0.0937   0.9135
   9.000   1.1145   0.05676   0.04957  -0.0356   0.0934   0.9149
   9.250   1.1195   0.06071   0.05390  -0.0339   0.0935   0.9163
   9.500   1.1250   0.06530   0.05877  -0.0328   0.0939   0.9177
   9.750   1.0314   0.07286   0.06767  -0.0220   0.1010   0.9176
  10.000   1.0037   0.07877   0.07387  -0.0202   0.1036   0.9185
  10.250   0.9944   0.08425   0.07947  -0.0203   0.1055   0.9196
  10.500   0.6452   0.12656   0.12257  -0.0260   0.1860   0.9124
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