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SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: SC(2)-0714 Supercritical airfoil (coordinates from Raymer w/ one correction) (nasasc2-0714-il)
Reynolds number: 50,000
Max Cl/Cd: 22.48 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-nasasc2-0714-il-50000-n5.txt
Download as CSV file: xf-nasasc2-0714-il-50000-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 =     0.050 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.750  -0.6068   0.10195   0.09306  -0.0526   1.0000   0.0832
 -12.500  -0.6458   0.09171   0.08277  -0.0579   1.0000   0.0830
 -12.250  -0.6850   0.08359   0.07460  -0.0611   1.0000   0.0827
 -12.000  -0.7222   0.07734   0.06824  -0.0624   1.0000   0.0825
 -11.750  -0.7565   0.07255   0.06334  -0.0619   1.0000   0.0824
 -11.500  -0.7888   0.06888   0.05957  -0.0597   1.0000   0.0824
 -11.250  -0.8176   0.06553   0.05606  -0.0574   1.0000   0.0825
 -11.000  -0.8387   0.06185   0.05212  -0.0562   1.0000   0.0830
 -10.750  -0.8510   0.05840   0.04837  -0.0552   1.0000   0.0838
 -10.500  -0.8437   0.05624   0.04618  -0.0540   1.0000   0.0851
 -10.250  -0.8375   0.05398   0.04380  -0.0530   1.0000   0.0863
 -10.000  -0.8300   0.05166   0.04130  -0.0520   1.0000   0.0877
  -9.750  -0.8203   0.04950   0.03894  -0.0512   1.0000   0.0897
  -9.500  -0.8094   0.04727   0.03643  -0.0507   1.0000   0.0923
  -9.250  -0.7964   0.04497   0.03371  -0.0503   1.0000   0.0951
  -9.000  -0.7797   0.04323   0.03190  -0.0494   1.0000   0.0973
  -8.750  -0.7619   0.04181   0.03042  -0.0483   1.0000   0.0997
  -8.500  -0.7437   0.04046   0.02897  -0.0474   1.0000   0.1030
  -8.250  -0.7247   0.03910   0.02737  -0.0466   1.0000   0.1072
  -8.000  -0.7054   0.03792   0.02613  -0.0453   1.0000   0.1109
  -7.750  -0.6863   0.03699   0.02524  -0.0437   1.0000   0.1146
  -7.500  -0.6668   0.03613   0.02431  -0.0421   1.0000   0.1194
  -7.250  -0.6473   0.03537   0.02346  -0.0404   1.0000   0.1251
  -7.000  -0.6288   0.03469   0.02288  -0.0386   1.0000   0.1309
  -6.750  -0.6096   0.03405   0.02214  -0.0368   1.0000   0.1378
  -6.500  -0.5914   0.03333   0.02156  -0.0353   1.0000   0.1455
  -6.250  -0.5722   0.03266   0.02087  -0.0340   1.0000   0.1558
  -6.000  -0.5531   0.03186   0.02021  -0.0331   1.0000   0.1674
  -5.750  -0.5327   0.03099   0.01948  -0.0328   1.0000   0.1832
  -5.500  -0.5105   0.03003   0.01872  -0.0330   1.0000   0.2061
  -5.250  -0.4855   0.02875   0.01785  -0.0345   1.0000   0.2446
  -5.000  -0.4583   0.02728   0.01725  -0.0365   1.0000   0.3344
  -4.750  -0.4546   0.02813   0.01906  -0.0291   1.0000   0.4332
  -4.500  -0.4491   0.02982   0.02102  -0.0213   1.0000   0.5002
  -4.000  -0.3944   0.03093   0.02174  -0.0222   1.0000   0.6004
  -3.750  -0.3760   0.03173   0.02245  -0.0196   1.0000   0.6216
  -3.500  -0.3574   0.03240   0.02302  -0.0173   1.0000   0.6404
  -3.250  -0.3402   0.03306   0.02360  -0.0146   1.0000   0.6582
  -3.000  -0.3259   0.03380   0.02430  -0.0110   1.0000   0.6768
  -2.750  -0.3131   0.03451   0.02499  -0.0070   1.0000   0.6963
  -2.500  -0.3005   0.03506   0.02551  -0.0031   1.0000   0.7149
  -2.250  -0.2870   0.03536   0.02578   0.0003   1.0000   0.7307
  -2.000  -0.2693   0.03541   0.02578   0.0021   1.0000   0.7429
  -1.750  -0.2466   0.03538   0.02568   0.0021   1.0000   0.7531
  -1.500  -0.2269   0.03523   0.02549   0.0031   0.9998   0.7595
  -1.250  -0.1921   0.03528   0.02547   0.0009   0.9945   0.7658
  -1.000  -0.1530   0.03537   0.02548  -0.0028   0.9892   0.7720
  -0.750  -0.1219   0.03537   0.02546  -0.0039   0.9833   0.7768
  -0.500  -0.0875   0.03543   0.02550  -0.0061   0.9767   0.7825
  -0.250  -0.0460   0.03562   0.02565  -0.0101   0.9699   0.7880
   0.000  -0.0145   0.03556   0.02561  -0.0114   0.9617   0.7913
   0.250   0.0235   0.03564   0.02571  -0.0142   0.9546   0.7948
   0.500   0.0580   0.03564   0.02574  -0.0164   0.9448   0.7984
   0.750   0.1008   0.03576   0.02589  -0.0203   0.9360   0.8016
   1.000   0.1388   0.03577   0.02597  -0.0232   0.9256   0.8041
   1.250   0.1712   0.03567   0.02595  -0.0245   0.9145   0.8066
   1.500   0.2104   0.03554   0.02591  -0.0270   0.9030   0.8094
   1.750   0.2542   0.03526   0.02575  -0.0300   0.8897   0.8122
   2.000   0.2953   0.03482   0.02542  -0.0323   0.8729   0.8151
   2.250   0.3317   0.03424   0.02497  -0.0336   0.8501   0.8183
   2.500   0.3726   0.03314   0.02402  -0.0345   0.8253   0.8211
   2.750   0.4052   0.03207   0.02309  -0.0339   0.7963   0.8238
   3.000   0.4383   0.03105   0.02223  -0.0335   0.7658   0.8260
   3.250   0.4678   0.03024   0.02157  -0.0327   0.7291   0.8283
   3.500   0.5027   0.02928   0.02072  -0.0324   0.6775   0.8307
   3.750   0.5706   0.02765   0.01838  -0.0352   0.5199   0.8324
   4.000   0.5956   0.02869   0.01840  -0.0345   0.3745   0.8343
   4.250   0.6101   0.02983   0.01896  -0.0328   0.2921   0.8360
   4.500   0.6282   0.03086   0.01962  -0.0319   0.2415   0.8376
   4.750   0.6500   0.03183   0.02034  -0.0315   0.2082   0.8395
   5.000   0.6744   0.03280   0.02112  -0.0315   0.1862   0.8417
   5.250   0.7023   0.03372   0.02193  -0.0321   0.1685   0.8440
   5.500   0.7338   0.03466   0.02283  -0.0332   0.1543   0.8463
   5.750   0.7698   0.03564   0.02386  -0.0349   0.1426   0.8485
   6.000   0.8028   0.03663   0.02481  -0.0361   0.1336   0.8503
   6.250   0.8350   0.03761   0.02587  -0.0370   0.1258   0.8521
   6.500   0.8671   0.03877   0.02701  -0.0381   0.1194   0.8539
   6.750   0.8982   0.03999   0.02842  -0.0389   0.1133   0.8560
   7.000   0.9285   0.04131   0.02971  -0.0398   0.1087   0.8583
   7.250   0.9577   0.04291   0.03152  -0.0406   0.1041   0.8608
   7.500   0.9850   0.04459   0.03346  -0.0411   0.0997   0.8633
   7.750   1.0088   0.04612   0.03511  -0.0410   0.0966   0.8657
   8.000   1.0333   0.04781   0.03677  -0.0411   0.0938   0.8681
   8.250   1.0492   0.04998   0.03950  -0.0400   0.0908   0.8705
   8.500   1.0655   0.05221   0.04208  -0.0391   0.0880   0.8726
   8.750   1.0818   0.05457   0.04473  -0.0384   0.0861   0.8748
   9.000   1.0974   0.05686   0.04722  -0.0378   0.0842   0.8772
   9.250   1.1137   0.05894   0.04938  -0.0373   0.0825   0.8797
   9.500   1.1124   0.06196   0.05285  -0.0347   0.0811   0.8822
   9.750   1.1034   0.06537   0.05677  -0.0317   0.0799   0.8847
  10.000   1.0895   0.06878   0.06058  -0.0285   0.0790   0.8871
  10.250   1.0726   0.07273   0.06490  -0.0260   0.0783   0.8895
  10.500   1.0511   0.07736   0.06989  -0.0244   0.0779   0.8915
  10.750   1.0230   0.08293   0.07578  -0.0239   0.0779   0.8930
  11.000   0.9871   0.08994   0.08310  -0.0253   0.0781   0.8942
  11.250   0.9428   0.09973   0.09315  -0.0301   0.0787   0.8949
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