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NASA SC(2)-0614 AIRFOIL (sc20614-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: NASA SC(2)-0614 AIRFOIL (sc20614-il)
Reynolds number: 50,000
Max Cl/Cd: 22.71 at α=7°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-sc20614-il-50000-n5.txt
Download as CSV file: xf-sc20614-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: NASA SC(2)-0614 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  -0.6037   0.10086   0.09196  -0.0472   1.0000   0.0868
 -12.250  -0.6589   0.08655   0.07759  -0.0559   1.0000   0.0860
 -12.000  -0.7126   0.07638   0.06726  -0.0610   1.0000   0.0853
 -11.750  -0.7521   0.07004   0.06075  -0.0624   1.0000   0.0850
 -11.500  -0.7830   0.06567   0.05623  -0.0616   1.0000   0.0851
 -11.250  -0.8092   0.06233   0.05276  -0.0594   1.0000   0.0854
 -11.000  -0.8256   0.05900   0.04923  -0.0582   1.0000   0.0860
 -10.750  -0.8357   0.05591   0.04589  -0.0568   1.0000   0.0871
 -10.500  -0.8414   0.05297   0.04262  -0.0554   1.0000   0.0886
 -10.250  -0.8435   0.05009   0.03933  -0.0542   1.0000   0.0905
 -10.000  -0.8299   0.04856   0.03787  -0.0530   1.0000   0.0927
  -9.750  -0.8185   0.04687   0.03610  -0.0518   1.0000   0.0951
  -9.500  -0.8070   0.04498   0.03399  -0.0506   1.0000   0.0978
  -9.250  -0.7950   0.04301   0.03168  -0.0496   1.0000   0.1011
  -9.000  -0.7793   0.04151   0.03014  -0.0484   1.0000   0.1042
  -8.750  -0.7627   0.04029   0.02891  -0.0472   1.0000   0.1077
  -8.500  -0.7458   0.03897   0.02742  -0.0461   1.0000   0.1119
  -8.250  -0.7281   0.03770   0.02599  -0.0448   1.0000   0.1163
  -8.000  -0.7100   0.03676   0.02514  -0.0434   1.0000   0.1206
  -7.750  -0.6916   0.03582   0.02411  -0.0420   1.0000   0.1260
  -7.500  -0.6730   0.03495   0.02319  -0.0403   1.0000   0.1315
  -7.250  -0.6547   0.03422   0.02251  -0.0387   1.0000   0.1374
  -6.750  -0.6188   0.03279   0.02111  -0.0353   1.0000   0.1518
  -6.500  -0.6006   0.03213   0.02037  -0.0338   1.0000   0.1607
  -6.250  -0.5833   0.03135   0.01976  -0.0326   1.0000   0.1705
  -6.000  -0.5650   0.03056   0.01907  -0.0316   1.0000   0.1831
  -5.750  -0.5459   0.02970   0.01836  -0.0310   1.0000   0.1994
  -5.500  -0.5251   0.02871   0.01757  -0.0311   1.0000   0.2237
  -5.250  -0.5021   0.02751   0.01675  -0.0320   1.0000   0.2640
  -5.000  -0.4781   0.02623   0.01623  -0.0331   1.0000   0.3435
  -4.750  -0.4695   0.02676   0.01762  -0.0275   1.0000   0.4348
  -4.500  -0.4600   0.02801   0.01915  -0.0215   1.0000   0.5038
  -4.250  -0.4365   0.02855   0.01955  -0.0208   1.0000   0.5573
  -4.000  -0.4096   0.02897   0.01978  -0.0214   1.0000   0.5969
  -3.750  -0.3932   0.02986   0.02059  -0.0182   1.0000   0.6185
  -3.500  -0.3762   0.03064   0.02130  -0.0154   1.0000   0.6396
  -3.000  -0.3417   0.03196   0.02248  -0.0103   1.0000   0.6787
  -2.750  -0.3279   0.03258   0.02306  -0.0067   1.0000   0.6951
  -2.500  -0.3137   0.03307   0.02352  -0.0034   1.0000   0.7113
  -2.250  -0.2983   0.03341   0.02382  -0.0007   1.0000   0.7266
  -2.000  -0.2716   0.03376   0.02411  -0.0002   0.9956   0.7415
  -1.750  -0.2473   0.03393   0.02423   0.0010   0.9910   0.7513
  -1.500  -0.2158   0.03395   0.02418  -0.0006   0.9862   0.7607
  -1.250  -0.1855   0.03399   0.02416  -0.0014   0.9816   0.7677
  -1.000  -0.1504   0.03399   0.02409  -0.0042   0.9765   0.7751
  -0.750  -0.1213   0.03395   0.02403  -0.0048   0.9707   0.7800
  -0.500  -0.0879   0.03396   0.02402  -0.0067   0.9649   0.7855
  -0.250  -0.0512   0.03401   0.02405  -0.0097   0.9578   0.7913
   0.000  -0.0167   0.03400   0.02404  -0.0115   0.9508   0.7952
   0.250   0.0156   0.03395   0.02402  -0.0131   0.9424   0.7988
   0.500   0.0522   0.03398   0.02407  -0.0156   0.9346   0.8026
   0.750   0.0896   0.03402   0.02414  -0.0184   0.9257   0.8064
   1.000   0.1249   0.03400   0.02419  -0.0205   0.9158   0.8098
   1.250   0.1644   0.03392   0.02418  -0.0230   0.9066   0.8128
   1.500   0.1961   0.03381   0.02417  -0.0241   0.8940   0.8159
   1.750   0.2345   0.03359   0.02404  -0.0263   0.8796   0.8185
   2.000   0.2778   0.03312   0.02368  -0.0287   0.8615   0.8212
   2.250   0.3259   0.03234   0.02302  -0.0315   0.8406   0.8240
   2.500   0.3722   0.03131   0.02214  -0.0332   0.8200   0.8265
   2.750   0.4007   0.03056   0.02153  -0.0323   0.7940   0.8291
   3.000   0.4424   0.02936   0.02047  -0.0328   0.7671   0.8313
   3.250   0.4675   0.02864   0.01989  -0.0312   0.7282   0.8338
   3.500   0.4943   0.02797   0.01932  -0.0299   0.6758   0.8367
   3.750   0.5440   0.02678   0.01782  -0.0309   0.5635   0.8393
   4.250   0.5901   0.02823   0.01759  -0.0280   0.3222   0.8448
   4.500   0.6057   0.02929   0.01820  -0.0266   0.2648   0.8477
   4.750   0.6258   0.03030   0.01891  -0.0260   0.2274   0.8508
   5.000   0.6499   0.03124   0.01970  -0.0260   0.2004   0.8540
   5.250   0.6768   0.03220   0.02053  -0.0265   0.1810   0.8571
   5.500   0.7018   0.03294   0.02123  -0.0262   0.1665   0.8600
   5.750   0.7307   0.03377   0.02205  -0.0266   0.1548   0.8629
   6.000   0.7616   0.03470   0.02286  -0.0275   0.1450   0.8657
   6.250   0.7952   0.03566   0.02396  -0.0286   0.1360   0.8686
   6.500   0.8282   0.03682   0.02504  -0.0299   0.1289   0.8718
   6.750   0.8570   0.03784   0.02627  -0.0302   0.1221   0.8750
   7.000   0.8849   0.03896   0.02734  -0.0305   0.1171   0.8785
   7.250   0.9130   0.04035   0.02895  -0.0309   0.1119   0.8820
   7.500   0.9401   0.04176   0.03052  -0.0313   0.1070   0.8854
   7.750   0.9671   0.04318   0.03188  -0.0319   0.1033   0.8884
   8.000   0.9877   0.04491   0.03400  -0.0312   0.0994   0.8918
   8.250   1.0081   0.04668   0.03606  -0.0307   0.0959   0.8957
   8.500   1.0296   0.04837   0.03787  -0.0305   0.0929   0.8998
   8.750   1.0494   0.05024   0.03982  -0.0302   0.0903   0.9038
   9.000   1.0579   0.05277   0.04289  -0.0284   0.0877   0.9080
   9.250   1.0672   0.05543   0.04596  -0.0270   0.0857   0.9122
   9.500   1.0764   0.05808   0.04891  -0.0258   0.0839   0.9163
   9.750   1.0853   0.06026   0.05128  -0.0245   0.0822   0.9204
  10.000   1.0976   0.06233   0.05341  -0.0238   0.0806   0.9250
  10.250   1.0885   0.06583   0.05733  -0.0214   0.0795   0.9296
  10.500   1.0674   0.06951   0.06145  -0.0181   0.0788   0.9347
  10.750   1.0436   0.07389   0.06622  -0.0161   0.0783   0.9403
  11.000   1.0155   0.07906   0.07175  -0.0154   0.0781   0.9457
  11.250   0.9814   0.08551   0.07852  -0.0164   0.0782   0.9511
  11.500   0.9416   0.09409   0.08737  -0.0203   0.0785   0.9559
  11.750   0.8944   0.10634   0.09984  -0.0284   0.0791   0.9593
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