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FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: FX 73-K-170/22 (fx73k170-il)
Reynolds number: 100,000
Max Cl/Cd: 26.3 at α=11°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx73k170-il-100000-n5.txt
Download as CSV file: xf-fx73k170-il-100000-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 =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.000  -0.0698   0.10032   0.09449  -0.1295   0.8754   0.0261
 -11.750  -0.0690   0.09578   0.08998  -0.1319   0.8723   0.0256
 -11.500  -0.0695   0.09086   0.08508  -0.1347   0.8693   0.0252
 -11.000  -0.1290   0.06730   0.06141  -0.1497   0.8633   0.0223
 -10.750  -0.1423   0.06295   0.05702  -0.1520   0.8591   0.0221
 -10.500  -0.1665   0.05803   0.05195  -0.1546   0.8545   0.0221
 -10.250  -0.1812   0.05447   0.04824  -0.1558   0.8505   0.0220
 -10.000  -0.1919   0.05217   0.04585  -0.1553   0.8460   0.0218
  -9.750  -0.2123   0.04962   0.04314  -0.1538   0.8407   0.0218
  -9.500  -0.2268   0.04770   0.04105  -0.1517   0.8364   0.0218
  -9.250  -0.2371   0.04590   0.03904  -0.1493   0.8322   0.0217
  -9.000  -0.2467   0.04408   0.03698  -0.1464   0.8270   0.0218
  -8.750  -0.2482   0.04202   0.03460  -0.1443   0.8232   0.0218
  -8.500  -0.2424   0.03999   0.03220  -0.1429   0.8203   0.0220
  -8.250  -0.2370   0.03839   0.03032  -0.1407   0.8164   0.0221
  -8.000  -0.2308   0.03689   0.02858  -0.1385   0.8118   0.0226
  -7.750  -0.2167   0.03564   0.02721  -0.1374   0.8085   0.0233
  -7.500  -0.1993   0.03472   0.02617  -0.1367   0.8060   0.0250
  -7.250  -0.1785   0.03337   0.02458  -0.1362   0.8040   0.0261
  -7.000  -0.1708   0.03271   0.02374  -0.1333   0.7988   0.0272
  -6.750  -0.1542   0.03169   0.02254  -0.1317   0.7950   0.0280
  -6.500  -0.1342   0.03053   0.02129  -0.1307   0.7922   0.0291
  -6.250  -0.1131   0.02955   0.02028  -0.1300   0.7901   0.0305
  -6.000  -0.0945   0.02885   0.01953  -0.1288   0.7876   0.0324
  -5.750  -0.0903   0.02879   0.01945  -0.1254   0.7816   0.0339
  -5.500  -0.0738   0.02818   0.01878  -0.1240   0.7782   0.0379
  -5.250  -0.0527   0.02753   0.01806  -0.1234   0.7757   0.0429
  -5.000  -0.0298   0.02676   0.01724  -0.1230   0.7738   0.0503
  -4.750  -0.0278   0.02687   0.01737  -0.1194   0.7676   0.0585
  -4.500  -0.0128   0.02639   0.01696  -0.1179   0.7637   0.0767
  -4.250   0.0071   0.02548   0.01635  -0.1174   0.7611   0.1330
  -4.000   0.0253   0.02390   0.01570  -0.1174   0.7590   0.3195
  -3.750   0.0250   0.02409   0.01656  -0.1131   0.7528   0.4462
  -3.500   0.0390   0.02465   0.01732  -0.1103   0.7486   0.5263
  -3.250   0.0639   0.02507   0.01760  -0.1093   0.7462   0.5731
  -3.000   0.0907   0.02549   0.01788  -0.1085   0.7444   0.6041
  -2.750   0.0985   0.02632   0.01866  -0.1051   0.7389   0.6234
  -2.500   0.1072   0.02707   0.01935  -0.1018   0.7336   0.6390
  -2.250   0.1311   0.02734   0.01951  -0.1007   0.7312   0.6535
  -2.000   0.1590   0.02739   0.01939  -0.1006   0.7295   0.6644
  -1.750   0.1548   0.02823   0.02022  -0.0959   0.7220   0.6714
  -1.500   0.1723   0.02851   0.02038  -0.0945   0.7179   0.6793
  -1.250   0.1987   0.02854   0.02030  -0.0942   0.7159   0.6859
  -1.000   0.2293   0.02845   0.02004  -0.0949   0.7143   0.6933
  -0.750   0.2177   0.02971   0.02133  -0.0895   0.7053   0.6977
  -0.500   0.2414   0.02984   0.02136  -0.0891   0.7024   0.7035
  -0.250   0.2707   0.02977   0.02115  -0.0895   0.7005   0.7093
   0.000   0.2999   0.02968   0.02099  -0.0898   0.6991   0.7133
   0.500   0.3187   0.03119   0.02238  -0.0857   0.6872   0.7237
   0.750   0.3466   0.03116   0.02230  -0.0858   0.6855   0.7272
   1.000   0.3769   0.03106   0.02214  -0.0863   0.6841   0.7311
   1.500   0.3977   0.03260   0.02360  -0.0827   0.6721   0.7400
   1.750   0.4269   0.03251   0.02349  -0.0829   0.6704   0.7433
   2.000   0.4578   0.03238   0.02332  -0.0835   0.6691   0.7471
   2.250   0.4509   0.03403   0.02497  -0.0799   0.6588   0.7517
   2.500   0.4801   0.03403   0.02493  -0.0803   0.6567   0.7558
   2.750   0.5108   0.03388   0.02478  -0.0808   0.6552   0.7592
   3.250   0.5364   0.03549   0.02640  -0.0782   0.6429   0.7679
   3.500   0.5673   0.03541   0.02631  -0.0789   0.6411   0.7720
   3.750   0.6002   0.03518   0.02609  -0.0797   0.6398   0.7757
   4.250   0.6272   0.03695   0.02791  -0.0775   0.6269   0.7853
   4.500   0.6596   0.03677   0.02776  -0.0783   0.6254   0.7895
   5.000   0.6895   0.03846   0.02954  -0.0767   0.6124   0.7998
   5.250   0.7223   0.03820   0.02936  -0.0775   0.6107   0.8050
   5.500   0.7568   0.03781   0.02903  -0.0784   0.6095   0.8109
   6.000   0.7881   0.03954   0.03093  -0.0772   0.5959   0.8234
   6.250   0.8223   0.03915   0.03063  -0.0781   0.5946   0.8314
   6.500   0.8218   0.04120   0.03280  -0.0763   0.5827   0.8402
   6.750   0.8563   0.04076   0.03248  -0.0773   0.5809   0.8506
   7.250   0.8960   0.04220   0.03424  -0.0775   0.5672   0.8830
   7.500   0.9364   0.04128   0.03354  -0.0796   0.5654   0.9838
   8.000   0.9638   0.04270   0.03506  -0.0771   0.5511   1.0000
   8.250   0.9997   0.04190   0.03434  -0.0778   0.5495   1.0000
   8.500   1.0009   0.04389   0.03640  -0.0763   0.5369   1.0000
   8.750   1.0367   0.04295   0.03556  -0.0768   0.5349   1.0000
   9.000   1.0392   0.04483   0.03753  -0.0753   0.5224   1.0000
   9.250   1.0758   0.04370   0.03650  -0.0758   0.5200   1.0000
   9.500   1.0799   0.04540   0.03829  -0.0744   0.5076   1.0000
   9.750   1.1188   0.04393   0.03696  -0.0748   0.5046   1.0000
  10.000   1.1240   0.04549   0.03861  -0.0734   0.4917   1.0000
  10.250   1.1353   0.04653   0.03975  -0.0723   0.4800   1.0000
  10.500   1.1650   0.04575   0.03908  -0.0720   0.4718   1.0000
  10.750   1.1889   0.04544   0.03888  -0.0714   0.4598   1.0000
  11.000   1.2057   0.04585   0.03937  -0.0705   0.4448   1.0000
  11.250   1.2193   0.04656   0.04012  -0.0694   0.4264   1.0000
  11.500   1.2323   0.04731   0.04089  -0.0682   0.4046   1.0000
  11.750   1.2471   0.04781   0.04131  -0.0670   0.3776   1.0000
  12.000   1.2570   0.04886   0.04227  -0.0657   0.3480   1.0000
  12.250   1.2614   0.05052   0.04378  -0.0642   0.3156   1.0000
  12.500   1.2642   0.05249   0.04564  -0.0628   0.2867   1.0000
  12.750   1.2633   0.05492   0.04791  -0.0614   0.2569   1.0000
  13.000   1.2612   0.05758   0.05045  -0.0602   0.2295   1.0000
  13.250   1.2581   0.06046   0.05321  -0.0591   0.2042   1.0000
  13.500   1.2533   0.06365   0.05629  -0.0581   0.1774   1.0000
  13.750   1.2490   0.06689   0.05943  -0.0573   0.1535   1.0000
  14.000   1.2436   0.07031   0.06274  -0.0566   0.1326   1.0000
  14.250   1.2398   0.07367   0.06606  -0.0561   0.1126   1.0000
  14.500   1.2355   0.07716   0.06949  -0.0557   0.0963   1.0000
  14.750   1.2313   0.08072   0.07300  -0.0554   0.0829   1.0000
  15.000   1.2287   0.08413   0.07641  -0.0552   0.0730   1.0000
  15.250   1.2256   0.08766   0.07995  -0.0551   0.0656   1.0000
  15.500   1.2240   0.09108   0.08341  -0.0551   0.0588   1.0000
  15.750   1.2224   0.09451   0.08688  -0.0552   0.0540   1.0000
  16.000   1.2220   0.09784   0.09031  -0.0554   0.0493   1.0000
  16.250   1.2186   0.10157   0.09401  -0.0558   0.0458   1.0000
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