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NASA SC(2)-0714 AIRFOIL (sc20714-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0714 AIRFOIL (sc20714-il)
Reynolds number: 50,000
Max Cl/Cd: 22.43 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20714-il-50000-n5.txt
Download as CSV file: xf-sc20714-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0714 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 =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.500  -0.5760   0.10645   0.09762  -0.0476   1.0000   0.0854
 -12.250  -0.6212   0.09333   0.08449  -0.0546   1.0000   0.0848
 -12.000  -0.7088   0.07867   0.06965  -0.0618   1.0000   0.0827
 -11.750  -0.7865   0.07065   0.06133  -0.0617   1.0000   0.0811
 -11.500  -0.8120   0.06763   0.05822  -0.0592   1.0000   0.0813
 -11.250  -0.8237   0.06492   0.05544  -0.0575   1.0000   0.0820
 -11.000  -0.8309   0.06221   0.05263  -0.0562   1.0000   0.0828
 -10.750  -0.8365   0.05940   0.04966  -0.0551   1.0000   0.0837
 -10.500  -0.8388   0.05657   0.04663  -0.0540   1.0000   0.0847
 -10.250  -0.8373   0.05382   0.04364  -0.0531   1.0000   0.0861
 -10.000  -0.8329   0.05115   0.04066  -0.0524   1.0000   0.0881
  -9.750  -0.8259   0.04838   0.03743  -0.0520   1.0000   0.0904
  -9.500  -0.8118   0.04644   0.03539  -0.0512   1.0000   0.0926
  -9.250  -0.7958   0.04487   0.03377  -0.0503   1.0000   0.0949
  -9.000  -0.7792   0.04320   0.03194  -0.0495   1.0000   0.0977
  -8.750  -0.7619   0.04152   0.02998  -0.0488   1.0000   0.1013
  -8.500  -0.7434   0.04007   0.02842  -0.0479   1.0000   0.1046
  -8.250  -0.7246   0.03896   0.02733  -0.0467   1.0000   0.1080
  -8.000  -0.7052   0.03787   0.02614  -0.0455   1.0000   0.1123
  -7.750  -0.6854   0.03684   0.02496  -0.0441   1.0000   0.1171
  -7.500  -0.6666   0.03605   0.02427  -0.0424   1.0000   0.1216
  -7.250  -0.6471   0.03533   0.02347  -0.0407   1.0000   0.1273
  -7.000  -0.6281   0.03465   0.02280  -0.0389   1.0000   0.1335
  -6.750  -0.6094   0.03399   0.02217  -0.0373   1.0000   0.1407
  -6.500  -0.5906   0.03332   0.02151  -0.0357   1.0000   0.1487
  -6.250  -0.5716   0.03262   0.02086  -0.0345   1.0000   0.1589
  -6.000  -0.5521   0.03183   0.02021  -0.0337   1.0000   0.1710
  -5.750  -0.5314   0.03097   0.01949  -0.0333   1.0000   0.1877
  -5.500  -0.5088   0.02998   0.01871  -0.0337   1.0000   0.2120
  -5.250  -0.4832   0.02866   0.01784  -0.0353   1.0000   0.2547
  -5.000  -0.4573   0.02735   0.01747  -0.0367   1.0000   0.3515
  -4.750  -0.4539   0.02836   0.01929  -0.0290   1.0000   0.4425
  -4.500  -0.4487   0.03008   0.02126  -0.0211   1.0000   0.5013
  -4.250  -0.4184   0.03045   0.02142  -0.0226   1.0000   0.5656
  -4.000  -0.3928   0.03114   0.02194  -0.0224   1.0000   0.6020
  -3.750  -0.3745   0.03197   0.02266  -0.0198   1.0000   0.6240
  -3.500  -0.3567   0.03273   0.02333  -0.0171   1.0000   0.6441
  -3.250  -0.3405   0.03343   0.02397  -0.0140   1.0000   0.6623
  -3.000  -0.3259   0.03411   0.02460  -0.0105   1.0000   0.6801
  -2.750  -0.3128   0.03474   0.02520  -0.0067   1.0000   0.6984
  -2.500  -0.2995   0.03521   0.02564  -0.0030   1.0000   0.7161
  -2.250  -0.2840   0.03550   0.02589  -0.0003   1.0000   0.7326
  -2.000  -0.2643   0.03562   0.02595   0.0009   1.0000   0.7465
  -1.750  -0.2475   0.03547   0.02576   0.0028   1.0000   0.7534
  -1.500  -0.2245   0.03538   0.02562   0.0027   1.0000   0.7612
  -1.250  -0.1935   0.03536   0.02554   0.0010   0.9968   0.7677
  -1.000  -0.1602   0.03540   0.02553  -0.0006   0.9912   0.7733
  -0.750  -0.1236   0.03547   0.02556  -0.0035   0.9851   0.7791
  -0.500  -0.0848   0.03561   0.02565  -0.0068   0.9796   0.7839
  -0.250  -0.0530   0.03557   0.02562  -0.0083   0.9720   0.7880
   0.000  -0.0164   0.03566   0.02570  -0.0108   0.9650   0.7922
   0.250   0.0226   0.03576   0.02582  -0.0141   0.9565   0.7964
   0.500   0.0614   0.03585   0.02593  -0.0173   0.9472   0.8002
   0.750   0.1000   0.03583   0.02597  -0.0197   0.9384   0.8034
   1.000   0.1312   0.03575   0.02596  -0.0210   0.9270   0.8069
   1.250   0.1688   0.03574   0.02603  -0.0235   0.9166   0.8103
   1.500   0.2127   0.03570   0.02608  -0.0271   0.9061   0.8130
   1.750   0.2523   0.03553   0.02601  -0.0298   0.8911   0.8154
   2.000   0.2915   0.03507   0.02569  -0.0317   0.8743   0.8176
   2.250   0.3356   0.03419   0.02494  -0.0336   0.8540   0.8198
   2.500   0.3692   0.03329   0.02417  -0.0337   0.8268   0.8219
   2.750   0.4095   0.03203   0.02307  -0.0343   0.7971   0.8236
   3.000   0.4438   0.03095   0.02214  -0.0340   0.7649   0.8258
   3.250   0.4718   0.03021   0.02154  -0.0331   0.7223   0.8283
   3.500   0.5103   0.02914   0.02052  -0.0331   0.6600   0.8306
   3.750   0.5807   0.02794   0.01835  -0.0367   0.4814   0.8320
   4.000   0.5976   0.02895   0.01857  -0.0348   0.3604   0.8335
   4.250   0.6120   0.03011   0.01915  -0.0331   0.2818   0.8352
   4.500   0.6309   0.03117   0.01984  -0.0322   0.2331   0.8371
   4.750   0.6535   0.03213   0.02056  -0.0320   0.2017   0.8394
   5.000   0.6792   0.03307   0.02136  -0.0322   0.1805   0.8417
   5.250   0.7087   0.03401   0.02221  -0.0330   0.1642   0.8440
   5.500   0.7418   0.03496   0.02314  -0.0344   0.1513   0.8460
   5.750   0.7771   0.03599   0.02411  -0.0361   0.1410   0.8477
   6.000   0.8103   0.03691   0.02509  -0.0372   0.1325   0.8493
   6.250   0.8432   0.03799   0.02617  -0.0383   0.1253   0.8511
   6.500   0.8749   0.03910   0.02741  -0.0391   0.1188   0.8532
   6.750   0.9068   0.04042   0.02862  -0.0403   0.1138   0.8556
   7.000   0.9360   0.04182   0.03034  -0.0408   0.1082   0.8581
   7.250   0.9649   0.04326   0.03188  -0.0416   0.1038   0.8606
   7.500   0.9937   0.04497   0.03365  -0.0425   0.1000   0.8628
   7.750   1.0148   0.04671   0.03577  -0.0419   0.0961   0.8648
   8.000   1.0367   0.04846   0.03774  -0.0416   0.0929   0.8668
   8.250   1.0597   0.05012   0.03943  -0.0417   0.0901   0.8688
   8.500   1.0750   0.05248   0.04218  -0.0406   0.0875   0.8711
   8.750   1.0864   0.05510   0.04526  -0.0392   0.0850   0.8735
   9.000   1.0974   0.05783   0.04836  -0.0381   0.0832   0.8759
   9.250   1.1074   0.06029   0.05108  -0.0368   0.0815   0.8784
   9.500   1.1184   0.06238   0.05330  -0.0356   0.0799   0.8810
   9.750   1.1235   0.06502   0.05613  -0.0340   0.0785   0.8835
  10.000   1.1076   0.06872   0.06035  -0.0305   0.0775   0.8856
  10.250   1.0878   0.07258   0.06462  -0.0274   0.0769   0.8877
  10.500   1.0649   0.07717   0.06959  -0.0254   0.0764   0.8894
  10.750   1.0374   0.08257   0.07534  -0.0246   0.0762   0.8908
  11.000   1.0045   0.08919   0.08227  -0.0256   0.0763   0.8919
  11.250   0.9643   0.09785   0.09121  -0.0292   0.0766   0.8927
  11.500   0.9179   0.11013   0.10370  -0.0372   0.0773   0.8929
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