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FX 78-K-150/20 (fx78k150-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: FX 78-K-150/20 (fx78k150-il)
Reynolds number: 200,000
Max Cl/Cd: 49.98 at α=7.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx78k150-il-200000-n5.txt
Download as CSV file: xf-fx78k150-il-200000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 78-K-150/20                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.1903   0.10058   0.09573  -0.0975   0.7454   0.0159
 -11.750  -0.1938   0.09566   0.09081  -0.0995   0.7445   0.0159
 -11.500  -0.2022   0.08978   0.08497  -0.1019   0.7437   0.0160
 -11.250  -0.2037   0.08581   0.08102  -0.1037   0.7429   0.0159
 -11.000  -0.2177   0.07931   0.07456  -0.1066   0.7420   0.0159
 -10.750  -0.2161   0.07645   0.07172  -0.1080   0.7409   0.0155
 -10.500  -0.2850   0.05702   0.05244  -0.1199   0.7397   0.0155
 -10.250  -0.3167   0.05079   0.04611  -0.1223   0.7381   0.0152
 -10.000  -0.3355   0.04752   0.04273  -0.1212   0.7365   0.0149
  -9.750  -0.3684   0.04354   0.03854  -0.1173   0.7348   0.0149
  -9.500  -0.3912   0.04058   0.03532  -0.1126   0.7333   0.0150
  -9.250  -0.4073   0.03709   0.03142  -0.1085   0.7318   0.0150
  -9.000  -0.4132   0.03400   0.02785  -0.1050   0.7306   0.0155
  -8.750  -0.4100   0.03148   0.02490  -0.1022   0.7293   0.0157
  -8.500  -0.4005   0.02942   0.02244  -0.1001   0.7283   0.0161
  -8.250  -0.3871   0.02792   0.02074  -0.0985   0.7274   0.0168
  -8.000  -0.3703   0.02702   0.01971  -0.0973   0.7261   0.0175
  -7.750  -0.3527   0.02609   0.01863  -0.0962   0.7246   0.0183
  -7.500  -0.3333   0.02536   0.01772  -0.0952   0.7231   0.0199
  -7.250  -0.3129   0.02447   0.01656  -0.0942   0.7216   0.0216
  -7.000  -0.2932   0.02351   0.01552  -0.0933   0.7201   0.0231
  -6.750  -0.2717   0.02294   0.01487  -0.0926   0.7186   0.0248
  -6.500  -0.2493   0.02234   0.01414  -0.0920   0.7173   0.0273
  -6.250  -0.2265   0.02174   0.01338  -0.0913   0.7162   0.0302
  -6.000  -0.2041   0.02123   0.01282  -0.0907   0.7153   0.0331
  -5.750  -0.1809   0.02075   0.01225  -0.0902   0.7144   0.0361
  -5.500  -0.1570   0.02035   0.01170  -0.0897   0.7136   0.0398
  -5.250  -0.1345   0.01983   0.01117  -0.0890   0.7128   0.0438
  -5.000  -0.1130   0.01965   0.01096  -0.0883   0.7108   0.0482
  -4.750  -0.0919   0.01941   0.01067  -0.0874   0.7086   0.0526
  -4.500  -0.0704   0.01912   0.01039  -0.0866   0.7068   0.0576
  -4.250  -0.0476   0.01894   0.01014  -0.0860   0.7053   0.0632
  -4.000  -0.0255   0.01867   0.00988  -0.0853   0.7040   0.0706
  -3.750  -0.0022   0.01847   0.00963  -0.0847   0.7028   0.0788
  -3.500   0.0210   0.01821   0.00936  -0.0841   0.7016   0.0900
  -3.250   0.0446   0.01795   0.00912  -0.0836   0.7006   0.1061
  -3.000   0.0680   0.01765   0.00890  -0.0830   0.6997   0.1310
  -2.750   0.0908   0.01732   0.00869  -0.0824   0.6989   0.1746
  -2.500   0.1089   0.01717   0.00880  -0.0812   0.6969   0.2363
  -2.250   0.1242   0.01712   0.00905  -0.0796   0.6941   0.3100
  -2.000   0.1381   0.01675   0.00912  -0.0775   0.6918   0.4215
  -1.750   0.1460   0.01606   0.00920  -0.0737   0.6899   0.6089
  -1.500   0.1665   0.01614   0.00986  -0.0711   0.6886   0.7778
  -1.250   0.1867   0.01636   0.01001  -0.0694   0.6874   0.8194
  -1.000   0.2070   0.01650   0.01006  -0.0679   0.6864   0.8424
  -0.750   0.2307   0.01664   0.01013  -0.0667   0.6856   0.8597
  -0.500   0.2550   0.01677   0.01023  -0.0655   0.6848   0.8793
  -0.250   0.2642   0.01748   0.01100  -0.0622   0.6802   0.8966
   0.000   0.2802   0.01784   0.01137  -0.0599   0.6774   0.9152
   0.250   0.3135   0.01803   0.01153  -0.0608   0.6760   0.9311
   0.500   0.3507   0.01811   0.01156  -0.0628   0.6747   0.9380
   0.750   0.3736   0.01811   0.01151  -0.0621   0.6735   0.9434
   1.000   0.4061   0.01810   0.01144  -0.0634   0.6725   0.9452
   1.250   0.4383   0.01809   0.01139  -0.0647   0.6717   0.9469
   1.500   0.4700   0.01806   0.01131  -0.0658   0.6710   0.9487
   2.000   0.4987   0.01935   0.01269  -0.0632   0.6618   0.9580
   2.250   0.5296   0.01942   0.01276  -0.0643   0.6604   0.9593
   2.500   0.5618   0.01940   0.01272  -0.0656   0.6593   0.9607
   2.750   0.5943   0.01934   0.01267  -0.0668   0.6584   0.9622
   3.000   0.6265   0.01927   0.01259  -0.0679   0.6576   0.9636
   3.250   0.6584   0.01917   0.01251  -0.0690   0.6568   0.9650
   4.250   0.7616   0.02066   0.01425  -0.0715   0.6442   0.9755
   4.500   0.7955   0.02050   0.01415  -0.0729   0.6434   0.9769
   4.750   0.8284   0.02037   0.01407  -0.0741   0.6422   0.9787
   5.250   0.8273   0.02391   0.01783  -0.0699   0.6232   1.0000
   6.250   0.9047   0.02401   0.01819  -0.0654   0.6140   1.0000
   6.750   0.8990   0.02742   0.02172  -0.0600   0.5938   1.0000
   7.000   0.9521   0.02430   0.01870  -0.0614   0.5890   1.0000
   7.250   0.9581   0.02546   0.01993  -0.0596   0.5776   1.0000
   7.500   0.9913   0.02361   0.01804  -0.0592   0.5407   1.0000
   7.750   1.0336   0.02068   0.01425  -0.0578   0.4213   1.0000
   8.000   1.0120   0.02346   0.01652  -0.0530   0.3476   1.0000
   8.250   0.9931   0.02638   0.01900  -0.0491   0.2779   1.0000
   8.500   0.9575   0.03058   0.02241  -0.0440   0.1596   1.0000
   8.750   0.9356   0.03407   0.02525  -0.0403   0.0610   1.0000
   9.000   0.9362   0.03618   0.02718  -0.0386   0.0320   1.0000
   9.250   0.9448   0.03773   0.02874  -0.0375   0.0247   1.0000
   9.500   0.9549   0.03921   0.03030  -0.0366   0.0214   1.0000
   9.750   0.9647   0.04073   0.03189  -0.0357   0.0189   1.0000
  10.000   0.9742   0.04230   0.03354  -0.0348   0.0179   1.0000
  10.250   0.9829   0.04396   0.03527  -0.0339   0.0174   1.0000
  10.500   0.9881   0.04596   0.03736  -0.0328   0.0163   1.0000
  10.750   0.9951   0.04783   0.03933  -0.0318   0.0156   1.0000
  11.000   1.0036   0.04956   0.04117  -0.0310   0.0155   1.0000
  11.250   1.0122   0.05128   0.04297  -0.0301   0.0149   1.0000
  11.500   1.0238   0.05276   0.04448  -0.0297   0.0129   1.0000
  11.750   1.0316   0.05457   0.04635  -0.0288   0.0128   1.0000
  12.000   1.0398   0.05634   0.04817  -0.0279   0.0124   1.0000
  12.250   1.0456   0.05815   0.04997  -0.0265   0.0116   1.0000
  12.500   1.0578   0.05946   0.05135  -0.0256   0.0117   1.0000
  12.750   1.0712   0.06070   0.05268  -0.0247   0.0113   1.0000
  13.000   1.0865   0.06172   0.05380  -0.0235   0.0113   1.0000
  13.250   1.1022   0.06282   0.05501  -0.0225   0.0111   1.0000
  13.500   1.1191   0.06388   0.05620  -0.0214   0.0109   1.0000
  13.750   1.1344   0.06522   0.05772  -0.0203   0.0105   1.0000
  14.000   1.1493   0.06674   0.05941  -0.0193   0.0105   1.0000
  14.250   1.1605   0.06877   0.06167  -0.0184   0.0101   1.0000
  14.500   1.1698   0.07116   0.06430  -0.0173   0.0100   1.0000
  14.750   1.1736   0.07374   0.06705  -0.0168   0.0095   1.0000
  15.000   1.1773   0.07701   0.07063  -0.0157   0.0099   1.0000
  15.250   1.1756   0.08026   0.07411  -0.0153   0.0095   1.0000
  15.500   1.1767   0.08273   0.07662  -0.0157   0.0088   1.0000
  15.750   1.1734   0.08638   0.08049  -0.0155   0.0088   1.0000
  16.000   1.1711   0.08945   0.08358  -0.0161   0.0083   1.0000
  16.250   1.1663   0.09333   0.08764  -0.0164   0.0082   1.0000
  16.500   1.1515   0.09919   0.09390  -0.0166   0.0085   1.0000
  16.750   1.1405   0.10430   0.09923  -0.0175   0.0085   1.0000
  17.000   1.1305   0.10929   0.10438  -0.0189   0.0084   1.0000
  17.250   1.1173   0.11509   0.11039  -0.0208   0.0083   1.0000
  17.500   1.1007   0.12172   0.11720  -0.0232   0.0082   1.0000
  17.750   1.0846   0.12853   0.12419  -0.0262   0.0081   1.0000
  18.000   1.0708   0.13552   0.13140  -0.0298   0.0082   1.0000
  18.250   1.0524   0.14374   0.13980  -0.0342   0.0081   1.0000
  18.500   1.0057   0.16168   0.15819  -0.0446   0.0087   1.0000
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