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FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=50,000 Ncrit=5


Details Polar file
Airfoil: FX 73-K-170/22 (fx73k170-il)
Reynolds number: 50,000
Max Cl/Cd: 13.3 at α=14.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73k170-il-50000-n5.txt
Download as CSV file: xf-fx73k170-il-50000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: FX 73-K-170/22                                  
  
 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
  ------ -------- --------- --------- -------- -------- --------
 -11.500  -0.1546   0.11579   0.10878  -0.1056   0.9351   0.0511
 -11.250  -0.1521   0.11122   0.10423  -0.1085   0.9315   0.0494
 -10.750  -0.1608   0.09734   0.09036  -0.1196   0.9254   0.0452
 -10.500  -0.1666   0.09338   0.08643  -0.1206   0.9200   0.0449
 -10.250  -0.1702   0.08875   0.08180  -0.1232   0.9155   0.0444
 -10.000  -0.1724   0.08379   0.07682  -0.1271   0.9118   0.0438
  -9.750  -0.1902   0.07954   0.07256  -0.1287   0.9059   0.0435
  -9.500  -0.2092   0.07590   0.06890  -0.1297   0.8995   0.0430
  -9.250  -0.2258   0.07176   0.06464  -0.1322   0.8948   0.0426
  -9.000  -0.2589   0.07095   0.06385  -0.1276   0.8856   0.0423
  -8.750  -0.2784   0.06803   0.06079  -0.1274   0.8802   0.0420
  -8.500  -0.3076   0.06760   0.06033  -0.1217   0.8717   0.0418
  -8.250  -0.3190   0.06500   0.05752  -0.1206   0.8666   0.0416
  -8.000  -0.3407   0.06366   0.05604  -0.1160   0.8598   0.0415
  -7.750  -0.3512   0.06172   0.05388  -0.1132   0.8541   0.0414
  -7.500  -0.3474   0.05865   0.05041  -0.1129   0.8506   0.0417
  -7.250  -0.3599   0.05748   0.04906  -0.1083   0.8440   0.0416
  -7.000  -0.3568   0.05530   0.04653  -0.1064   0.8394   0.0420
  -6.750  -0.3415   0.05285   0.04365  -0.1062   0.8364   0.0426
  -6.500  -0.3233   0.05071   0.04100  -0.1059   0.8336   0.0443
  -6.250  -0.3271   0.04989   0.03989  -0.1017   0.8275   0.0452
  -6.000  -0.3101   0.04836   0.03827  -0.1010   0.8239   0.0476
  -5.750  -0.2864   0.04706   0.03677  -0.1009   0.8213   0.0498
  -5.500  -0.2580   0.04568   0.03513  -0.1008   0.8193   0.0530
  -5.250  -0.2585   0.04539   0.03471  -0.0966   0.8136   0.0547
  -5.000  -0.2419   0.04465   0.03388  -0.0948   0.8099   0.0587
  -4.750  -0.2202   0.04392   0.03308  -0.0940   0.8069   0.0651
  -4.500  -0.1959   0.04306   0.03209  -0.0934   0.8046   0.0721
  -4.250  -0.1913   0.04280   0.03179  -0.0904   0.7998   0.0799
  -4.000  -0.1792   0.04222   0.03122  -0.0888   0.7954   0.0916
  -3.750  -0.1589   0.04120   0.03034  -0.0887   0.7922   0.1192
  -3.500  -0.1353   0.03912   0.02918  -0.0904   0.7899   0.2359
  -3.250  -0.1343   0.03887   0.03047  -0.0853   0.7860   0.4749
  -3.000  -0.1272   0.03988   0.03140  -0.0814   0.7808   0.5673
  -2.750  -0.1123   0.04097   0.03232  -0.0780   0.7770   0.6204
  -2.500  -0.0970   0.04207   0.03331  -0.0737   0.7742   0.6651
  -2.250  -0.0945   0.04286   0.03401  -0.0688   0.7692   0.6932
  -2.000  -0.0881   0.04340   0.03446  -0.0643   0.7646   0.7144
  -1.750  -0.0707   0.04371   0.03455  -0.0622   0.7612   0.7324
  -1.500  -0.0465   0.04389   0.03450  -0.0615   0.7586   0.7462
  -1.250  -0.0380   0.04424   0.03468  -0.0593   0.7535   0.7575
  -1.000  -0.0226   0.04451   0.03478  -0.0579   0.7490   0.7678
  -0.750   0.0006   0.04470   0.03476  -0.0575   0.7457   0.7769
  -0.500   0.0304   0.04490   0.03472  -0.0585   0.7431   0.7864
  -0.250   0.0356   0.04533   0.03507  -0.0559   0.7373   0.7937
   0.000   0.0567   0.04567   0.03524  -0.0559   0.7329   0.8018
   0.250   0.0822   0.04591   0.03531  -0.0560   0.7298   0.8086
   0.500   0.1080   0.04627   0.03551  -0.0566   0.7267   0.8161
   0.750   0.1161   0.04679   0.03597  -0.0548   0.7203   0.8224
   1.000   0.1411   0.04716   0.03620  -0.0553   0.7164   0.8291
   1.250   0.1716   0.04747   0.03637  -0.0564   0.7136   0.8355
   1.500   0.1809   0.04813   0.03699  -0.0550   0.7073   0.8421
   1.750   0.2038   0.04863   0.03740  -0.0553   0.7027   0.8488
   2.000   0.2329   0.04899   0.03768  -0.0562   0.6996   0.8553
   2.250   0.2483   0.04969   0.03833  -0.0558   0.6939   0.8627
   2.500   0.2692   0.05023   0.03883  -0.0559   0.6885   0.8699
   2.750   0.2992   0.05067   0.03922  -0.0571   0.6852   0.8777
   3.000   0.3160   0.05141   0.03997  -0.0569   0.6794   0.8862
   3.250   0.3382   0.05207   0.04063  -0.0574   0.6738   0.8956
   3.500   0.3710   0.05252   0.04109  -0.0592   0.6704   0.9066
   3.750   0.3892   0.05346   0.04207  -0.0597   0.6635   0.9198
   4.250   0.4523   0.05447   0.04312  -0.0635   0.6548   1.0000
   4.500   0.4614   0.05580   0.04444  -0.0632   0.6463   1.0000
   4.750   0.4916   0.05650   0.04511  -0.0647   0.6419   1.0000
   5.000   0.5120   0.05752   0.04613  -0.0654   0.6358   1.0000
   5.250   0.5321   0.05856   0.04717  -0.0659   0.6292   1.0000
   5.500   0.5654   0.05910   0.04770  -0.0675   0.6255   1.0000
   5.750   0.5741   0.06058   0.04920  -0.0671   0.6164   1.0000
   6.000   0.6028   0.06129   0.04994  -0.0682   0.6119   1.0000
   6.250   0.6175   0.06260   0.05127  -0.0682   0.6045   1.0000
   6.500   0.6403   0.06349   0.05220  -0.0687   0.5982   1.0000
   6.750   0.6742   0.06385   0.05259  -0.0700   0.5948   1.0000
   7.000   0.6780   0.06566   0.05444  -0.0690   0.5842   1.0000
   7.250   0.7100   0.06604   0.05490  -0.0700   0.5803   1.0000
   7.500   0.7148   0.06785   0.05677  -0.0692   0.5698   1.0000
   7.750   0.7462   0.06814   0.05712  -0.0700   0.5655   1.0000
   8.000   0.7512   0.06998   0.05906  -0.0691   0.5549   1.0000
   8.250   0.7820   0.07025   0.05942  -0.0697   0.5505   1.0000
   8.500   0.7867   0.07214   0.06139  -0.0689   0.5396   1.0000
   8.750   0.8183   0.07221   0.06157  -0.0694   0.5352   1.0000
   9.000   0.8222   0.07423   0.06368  -0.0686   0.5238   1.0000
   9.250   0.8559   0.07397   0.06358  -0.0690   0.5196   1.0000
   9.500   0.8587   0.07607   0.06578  -0.0681   0.5076   1.0000
  10.000   0.8962   0.07769   0.06770  -0.0676   0.4913   1.0000
  10.250   0.9022   0.07962   0.06975  -0.0669   0.4797   1.0000
  10.500   0.9358   0.07892   0.06923  -0.0669   0.4748   1.0000
  10.750   0.9400   0.08096   0.07141  -0.0661   0.4621   1.0000
  11.000   0.9485   0.08261   0.07320  -0.0655   0.4505   1.0000
  11.250   0.9813   0.08163   0.07245  -0.0651   0.4449   1.0000
  11.500   0.9875   0.08343   0.07440  -0.0644   0.4318   1.0000
  11.750   0.9964   0.08500   0.07614  -0.0637   0.4195   1.0000
  12.250   1.0406   0.08458   0.07615  -0.0621   0.4005   1.0000
  12.500   1.0512   0.08566   0.07741  -0.0613   0.3871   1.0000
  13.000   1.0834   0.08603   0.07818  -0.0593   0.3606   1.0000
  13.250   1.1035   0.08550   0.07785  -0.0581   0.3461   1.0000
  13.500   1.1226   0.08500   0.07756  -0.0568   0.3288   1.0000
  14.500   1.1681   0.08785   0.08045  -0.0527   0.2274   1.0000
  14.750   1.1683   0.09047   0.08291  -0.0522   0.2002   1.0000
  15.000   1.1652   0.09373   0.08601  -0.0520   0.1757   1.0000
  15.250   1.1608   0.09743   0.08964  -0.0521   0.1542   1.0000
  15.500   1.1563   0.10120   0.09328  -0.0523   0.1361   1.0000
  15.750   1.1530   0.10488   0.09685  -0.0526   0.1213   1.0000
  16.000   1.1501   0.10859   0.10050  -0.0531   0.1082   1.0000
  16.250   1.1496   0.11203   0.10392  -0.0535   0.0976   1.0000
  16.500   1.1508   0.11520   0.10705  -0.0539   0.0891   1.0000
  16.750   1.1524   0.11833   0.11018  -0.0544   0.0814   1.0000
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