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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=5


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: 31.06 at α=6°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nasasc2-0714-il-100000-n5.txt
Download as CSV file: xf-nasasc2-0714-il-100000-n5.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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.750  -0.7678   0.07565   0.06881  -0.0683   1.0000   0.0521
 -13.500  -0.8104   0.06834   0.06126  -0.0706   1.0000   0.0520
 -13.250  -0.8413   0.06334   0.05607  -0.0707   1.0000   0.0521
 -13.000  -0.8667   0.05947   0.05200  -0.0696   1.0000   0.0523
 -12.750  -0.8888   0.05631   0.04866  -0.0676   1.0000   0.0525
 -12.500  -0.9094   0.05370   0.04588  -0.0647   1.0000   0.0528
 -12.250  -0.9296   0.05154   0.04355  -0.0610   1.0000   0.0532
 -12.000  -0.9439   0.04925   0.04106  -0.0581   1.0000   0.0536
 -11.750  -0.9513   0.04680   0.03831  -0.0563   1.0000   0.0543
 -11.500  -0.9520   0.04455   0.03579  -0.0549   1.0000   0.0552
 -11.250  -0.9415   0.04325   0.03451  -0.0538   1.0000   0.0561
 -11.000  -0.9309   0.04198   0.03320  -0.0527   1.0000   0.0571
 -10.750  -0.9195   0.04063   0.03174  -0.0517   1.0000   0.0583
 -10.500  -0.9068   0.03917   0.03014  -0.0508   1.0000   0.0596
 -10.250  -0.8927   0.03766   0.02843  -0.0499   1.0000   0.0610
 -10.000  -0.8771   0.03622   0.02675  -0.0491   1.0000   0.0625
  -9.750  -0.8602   0.03498   0.02540  -0.0482   1.0000   0.0640
  -9.500  -0.8423   0.03406   0.02452  -0.0475   1.0000   0.0656
  -9.250  -0.8236   0.03315   0.02357  -0.0469   1.0000   0.0674
  -9.000  -0.8043   0.03221   0.02254  -0.0462   1.0000   0.0694
  -8.750  -0.7843   0.03128   0.02148  -0.0454   1.0000   0.0714
  -8.500  -0.7641   0.03041   0.02053  -0.0447   1.0000   0.0735
  -8.250  -0.7436   0.02966   0.01984  -0.0443   1.0000   0.0759
  -8.000  -0.7222   0.02896   0.01914  -0.0439   1.0000   0.0786
  -7.750  -0.7004   0.02829   0.01840  -0.0434   1.0000   0.0816
  -7.500  -0.6785   0.02761   0.01768  -0.0428   1.0000   0.0844
  -7.250  -0.6557   0.02695   0.01710  -0.0428   1.0000   0.0879
  -7.000  -0.6322   0.02640   0.01654  -0.0427   1.0000   0.0923
  -6.750  -0.6083   0.02583   0.01597  -0.0426   1.0000   0.0969
  -6.500  -0.5781   0.02523   0.01543  -0.0440   0.9985   0.1025
  -6.250  -0.5460   0.02474   0.01494  -0.0456   0.9966   0.1104
  -6.000  -0.5133   0.02421   0.01449  -0.0474   0.9948   0.1200
  -5.750  -0.4793   0.02372   0.01410  -0.0495   0.9933   0.1319
  -5.500  -0.4459   0.02324   0.01373  -0.0515   0.9913   0.1486
  -5.250  -0.4120   0.02274   0.01338  -0.0537   0.9893   0.1732
  -5.000  -0.3758   0.02207   0.01302  -0.0567   0.9878   0.2188
  -4.750  -0.3313   0.02088   0.01255  -0.0624   0.9873   0.3317
  -4.500  -0.3055   0.02101   0.01363  -0.0615   0.9848   0.4761
  -4.000  -0.2542   0.02258   0.01540  -0.0587   0.9779   0.5746
  -3.750  -0.2185   0.02289   0.01560  -0.0607   0.9748   0.6000
  -3.250  -0.1566   0.02408   0.01668  -0.0610   0.9683   0.6254
  -3.000  -0.1300   0.02448   0.01703  -0.0606   0.9634   0.6367
  -2.750  -0.1033   0.02517   0.01771  -0.0597   0.9589   0.6517
  -2.500  -0.0823   0.02616   0.01873  -0.0565   0.9548   0.6628
  -2.250  -0.0624   0.02677   0.01936  -0.0540   0.9496   0.6730
  -2.000  -0.0353   0.02704   0.01961  -0.0538   0.9449   0.6817
  -1.750  -0.0006   0.02709   0.01962  -0.0554   0.9413   0.6875
  -1.500   0.0330   0.02716   0.01969  -0.0564   0.9382   0.6904
  -1.250   0.0567   0.02715   0.01969  -0.0558   0.9311   0.6940
  -1.000   0.0937   0.02706   0.01958  -0.0581   0.9266   0.6987
  -0.750   0.1384   0.02688   0.01938  -0.0621   0.9230   0.7038
  -0.500   0.1604   0.02685   0.01940  -0.0606   0.9137   0.7064
  -0.250   0.1965   0.02670   0.01928  -0.0619   0.9084   0.7091
   0.000   0.2276   0.02653   0.01915  -0.0628   0.9003   0.7117
   0.250   0.2673   0.02621   0.01887  -0.0651   0.8931   0.7147
   0.500   0.3071   0.02581   0.01850  -0.0677   0.8831   0.7183
   0.750   0.3571   0.02489   0.01763  -0.0713   0.8708   0.7208
   1.000   0.3906   0.02404   0.01683  -0.0711   0.8517   0.7221
   1.250   0.4217   0.02335   0.01621  -0.0707   0.8333   0.7236
   1.500   0.4515   0.02287   0.01580  -0.0704   0.8154   0.7254
   1.750   0.4824   0.02236   0.01537  -0.0702   0.7915   0.7275
   2.000   0.5172   0.02172   0.01474  -0.0706   0.7512   0.7299
   2.250   0.5955   0.02066   0.01301  -0.0778   0.6055   0.7317
   2.500   0.6252   0.02146   0.01293  -0.0780   0.4522   0.7346
   2.750   0.6491   0.02243   0.01323  -0.0780   0.3381   0.7377
   3.000   0.6671   0.02318   0.01358  -0.0763   0.2651   0.7393
   3.250   0.6875   0.02385   0.01396  -0.0751   0.2129   0.7410
   3.500   0.7099   0.02445   0.01435  -0.0744   0.1773   0.7427
   3.750   0.7328   0.02505   0.01479  -0.0737   0.1542   0.7447
   4.000   0.7569   0.02563   0.01527  -0.0734   0.1382   0.7468
   4.250   0.7823   0.02618   0.01579  -0.0733   0.1256   0.7488
   4.500   0.8082   0.02677   0.01634  -0.0734   0.1160   0.7506
   4.750   0.8344   0.02743   0.01692  -0.0737   0.1084   0.7526
   5.000   0.8626   0.02807   0.01759  -0.0743   0.1017   0.7545
   5.250   0.8855   0.02868   0.01819  -0.0736   0.0966   0.7558
   5.500   0.9077   0.02940   0.01889  -0.0728   0.0924   0.7572
   5.750   0.9310   0.03002   0.01961  -0.0721   0.0880   0.7588
   6.000   0.9539   0.03071   0.02030  -0.0714   0.0843   0.7607
   6.250   0.9779   0.03158   0.02114  -0.0710   0.0813   0.7627
   6.500   1.0038   0.03236   0.02206  -0.0709   0.0779   0.7647
   6.750   1.0294   0.03317   0.02291  -0.0710   0.0747   0.7666
   7.000   1.0551   0.03411   0.02379  -0.0712   0.0722   0.7685
   7.250   1.0834   0.03525   0.02504  -0.0717   0.0699   0.7705
   7.500   1.1094   0.03632   0.02628  -0.0718   0.0673   0.7722
   7.750   1.1310   0.03726   0.02731  -0.0710   0.0651   0.7736
   8.000   1.1525   0.03823   0.02828  -0.0703   0.0633   0.7751
   8.250   1.1754   0.03956   0.02966  -0.0698   0.0618   0.7769
   8.500   1.1970   0.04107   0.03147  -0.0691   0.0602   0.7789
   8.750   1.2171   0.04261   0.03325  -0.0682   0.0586   0.7811
   9.000   1.2362   0.04405   0.03487  -0.0674   0.0570   0.7835
   9.250   1.2550   0.04541   0.03633  -0.0667   0.0557   0.7858
   9.500   1.2747   0.04681   0.03776  -0.0663   0.0545   0.7880
   9.750   1.2871   0.04865   0.03981  -0.0645   0.0535   0.7894
  10.000   1.2928   0.05093   0.04251  -0.0618   0.0525   0.7910
  10.250   1.2946   0.05330   0.04525  -0.0588   0.0517   0.7926
  10.500   1.2919   0.05570   0.04798  -0.0554   0.0511   0.7944
  10.750   1.2886   0.05835   0.05094  -0.0524   0.0504   0.7963
  11.000   1.2835   0.06113   0.05402  -0.0497   0.0498   0.7983
  11.250   1.2769   0.06405   0.05719  -0.0473   0.0492   0.8004
  11.500   1.2694   0.06712   0.06049  -0.0453   0.0487   0.8025
  11.750   1.2585   0.07046   0.06406  -0.0436   0.0483   0.8042
  12.000   1.2452   0.07404   0.06786  -0.0421   0.0479   0.8057
  12.250   1.2282   0.07831   0.07237  -0.0414   0.0476   0.8071
  12.500   1.2066   0.08352   0.07782  -0.0417   0.0474   0.8084
  12.750   1.1567   0.09354   0.08827  -0.0456   0.0476   0.8089
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