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FX 78-K-140/20 (fx78k140-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 78-K-140/20 (fx78k140-il)
Reynolds number: 200,000
Max Cl/Cd: 53.83 at α=8°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx78k140-il-200000-n5.txt
Download as CSV file: xf-fx78k140-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-140/20                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1843   0.09416   0.08972  -0.0801   0.7545   0.0135
 -10.000  -0.1853   0.09012   0.08571  -0.0817   0.7535   0.0132
  -9.750  -0.1884   0.08580   0.08143  -0.0835   0.7525   0.0133
  -9.500  -0.1920   0.08160   0.07725  -0.0853   0.7516   0.0131
  -9.250  -0.1949   0.07779   0.07347  -0.0870   0.7502   0.0126
  -9.000  -0.2033   0.07315   0.06892  -0.0894   0.7483   0.0124
  -8.750  -0.2180   0.06775   0.06361  -0.0931   0.7464   0.0120
  -8.500  -0.2336   0.06337   0.05925  -0.0948   0.7445   0.0121
  -8.250  -0.2589   0.05855   0.05437  -0.0935   0.7428   0.0116
  -8.000  -0.2734   0.05388   0.04958  -0.0923   0.7413   0.0114
  -7.750  -0.2919   0.04745   0.04286  -0.0897   0.7399   0.0111
  -7.500  -0.3016   0.04228   0.03734  -0.0866   0.7386   0.0111
  -7.250  -0.2979   0.03967   0.03447  -0.0844   0.7376   0.0116
  -7.000  -0.2990   0.03544   0.02981  -0.0811   0.7355   0.0115
  -6.750  -0.2884   0.03345   0.02754  -0.0792   0.7336   0.0123
  -6.500  -0.2787   0.03064   0.02429  -0.0768   0.7319   0.0126
  -6.250  -0.2626   0.02896   0.02227  -0.0751   0.7302   0.0136
  -6.000  -0.2441   0.02740   0.02031  -0.0736   0.7288   0.0153
  -5.750  -0.2243   0.02577   0.01830  -0.0723   0.7275   0.0158
  -5.500  -0.2041   0.02366   0.01583  -0.0710   0.7264   0.0168
  -5.250  -0.1818   0.02247   0.01446  -0.0702   0.7254   0.0180
  -5.000  -0.1582   0.02162   0.01348  -0.0695   0.7246   0.0193
  -4.750  -0.1340   0.02106   0.01276  -0.0690   0.7238   0.0217
  -4.500  -0.1117   0.02066   0.01227  -0.0684   0.7211   0.0237
  -4.250  -0.0908   0.01997   0.01154  -0.0674   0.7188   0.0269
  -4.000  -0.0685   0.01957   0.01109  -0.0667   0.7170   0.0298
  -3.750  -0.0449   0.01934   0.01077  -0.0661   0.7155   0.0347
  -3.500  -0.0231   0.01888   0.01030  -0.0652   0.7142   0.0415
  -3.250   0.0001   0.01855   0.00990  -0.0644   0.7130   0.0502
  -3.000   0.0238   0.01823   0.00952  -0.0637   0.7120   0.0617
  -2.750   0.0474   0.01792   0.00917  -0.0630   0.7110   0.0751
  -2.500   0.0707   0.01759   0.00889  -0.0624   0.7102   0.0972
  -2.250   0.0873   0.01777   0.00929  -0.0612   0.7061   0.1354
  -2.000   0.1052   0.01750   0.00931  -0.0599   0.7034   0.2128
  -1.750   0.1219   0.01706   0.00923  -0.0582   0.7016   0.3263
  -1.500   0.1308   0.01627   0.00915  -0.0548   0.7000   0.5167
  -1.250   0.1628   0.01543   0.00935  -0.0550   0.6992   0.8148
  -1.000   0.2215   0.01548   0.00937  -0.0611   0.6987   0.8850
  -0.750   0.2786   0.01564   0.00943  -0.0669   0.6982   0.9196
  -0.500   0.3459   0.01601   0.00968  -0.0743   0.6979   0.9474
  -0.250   0.3989   0.01618   0.00973  -0.0794   0.6974   0.9599
   0.000   0.4317   0.01622   0.00967  -0.0806   0.6966   0.9671
   0.250   0.4645   0.01689   0.01037  -0.0831   0.6916   0.9712
   0.500   0.4959   0.01707   0.01051  -0.0845   0.6894   0.9753
   0.750   0.5249   0.01716   0.01056  -0.0853   0.6877   0.9798
   1.000   0.5592   0.01712   0.01047  -0.0870   0.6864   0.9824
   1.250   0.5921   0.01710   0.01042  -0.0885   0.6853   0.9855
   1.500   0.6232   0.01707   0.01036  -0.0895   0.6843   0.9888
   1.750   0.6566   0.01696   0.01022  -0.0910   0.6835   0.9912
   2.250   0.7167   0.01782   0.01119  -0.0943   0.6751   0.9986
   2.500   0.7457   0.01776   0.01113  -0.0949   0.6733   1.0000
   2.750   0.7674   0.01769   0.01106  -0.0940   0.6718   1.0000
   3.000   0.7905   0.01753   0.01090  -0.0932   0.6706   1.0000
   3.500   0.8146   0.01854   0.01206  -0.0891   0.6610   1.0000
   3.750   0.8360   0.01846   0.01200  -0.0880   0.6591   1.0000
   4.000   0.8599   0.01824   0.01181  -0.0873   0.6577   1.0000
   4.250   0.8852   0.01798   0.01157  -0.0867   0.6565   1.0000
   4.750   0.9024   0.01911   0.01287  -0.0813   0.6455   1.0000
   5.000   0.9279   0.01886   0.01267  -0.0808   0.6440   1.0000
   5.250   0.9547   0.01854   0.01240  -0.0804   0.6424   1.0000
   5.750   0.9705   0.01957   0.01360  -0.0746   0.6307   1.0000
   6.000   0.9999   0.01918   0.01331  -0.0746   0.6294   1.0000
   6.500   0.9985   0.02080   0.01507  -0.0665   0.6144   1.0000
   7.500   1.0266   0.02260   0.01711  -0.0550   0.5711   1.0000
   7.750   1.0652   0.02064   0.01509  -0.0549   0.5315   1.0000
   8.000   1.0793   0.02005   0.01373  -0.0513   0.4299   1.0000
   8.250   1.0519   0.02264   0.01574  -0.0448   0.3515   1.0000
   8.500   1.0282   0.02545   0.01803  -0.0396   0.2772   1.0000
   8.750   1.0190   0.02762   0.01989  -0.0363   0.2246   1.0000
   9.000   1.0019   0.03044   0.02221  -0.0324   0.1497   1.0000
   9.250   0.9828   0.03363   0.02479  -0.0286   0.0624   1.0000
   9.500   0.9769   0.03610   0.02696  -0.0260   0.0222   1.0000
   9.750   0.9859   0.03746   0.02837  -0.0248   0.0181   1.0000
  10.000   0.9923   0.03912   0.03008  -0.0233   0.0145   1.0000
  10.250   1.0007   0.04064   0.03172  -0.0220   0.0124   1.0000
  10.500   1.0080   0.04228   0.03348  -0.0207   0.0112   1.0000
  10.750   1.0120   0.04422   0.03552  -0.0194   0.0099   1.0000
  11.000   1.0132   0.04652   0.03793  -0.0178   0.0092   1.0000
  11.250   1.0214   0.04818   0.03974  -0.0168   0.0085   1.0000
  11.500   1.0239   0.05039   0.04205  -0.0155   0.0089   1.0000
  11.750   1.0360   0.05171   0.04345  -0.0150   0.0076   1.0000
  12.000   1.0399   0.05384   0.04566  -0.0139   0.0067   1.0000
  12.250   1.0472   0.05566   0.04756  -0.0129   0.0067   1.0000
  12.500   1.0543   0.05749   0.04950  -0.0118   0.0071   1.0000
  12.750   1.0599   0.05948   0.05155  -0.0107   0.0064   1.0000
  13.000   1.0676   0.06128   0.05342  -0.0096   0.0061   1.0000
  13.250   1.0771   0.06291   0.05513  -0.0086   0.0060   1.0000
  13.500   1.0875   0.06451   0.05684  -0.0077   0.0060   1.0000
  13.750   1.1019   0.06600   0.05844  -0.0053   0.0056   1.0000
  14.000   1.1127   0.06792   0.06053  -0.0042   0.0056   1.0000
  14.250   1.1180   0.07027   0.06313  -0.0036   0.0055   1.0000
  14.750   1.1257   0.07581   0.06909  -0.0021   0.0055   1.0000
  15.000   1.1223   0.07966   0.07325  -0.0013   0.0054   1.0000
  15.250   1.1186   0.08326   0.07707  -0.0012   0.0054   1.0000
  15.500   1.1096   0.08797   0.08206  -0.0010   0.0054   1.0000
  15.750   1.1073   0.09147   0.08568  -0.0012   0.0055   1.0000
  16.000   1.0921   0.09723   0.09173  -0.0018   0.0055   1.0000
  16.250   1.0820   0.10214   0.09684  -0.0029   0.0055   1.0000
  16.500   1.0712   0.10736   0.10225  -0.0042   0.0055   1.0000
  16.750   1.0577   0.11331   0.10840  -0.0061   0.0055   1.0000
  17.000   1.0426   0.11981   0.11510  -0.0086   0.0055   1.0000
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