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FX 73-K-170/22 (fx73k170-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: FX 73-K-170/22 (fx73k170-il)
Reynolds number: 200,000
Max Cl/Cd: 62.98 at α=8.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx73k170-il-200000.txt
Download as CSV file: xf-fx73k170-il-200000.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 =     0.200 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -13.250   0.0614   0.10247   0.09846  -0.1362   0.8882   0.0518
 -13.000  -0.0501   0.11190   0.10775  -0.1388   0.9047   0.0488
 -12.750  -0.0313   0.10971   0.10554  -0.1381   0.9017   0.0501
 -12.500  -0.0195   0.10683   0.10264  -0.1395   0.8985   0.0514
 -12.250  -0.0093   0.10380   0.09959  -0.1417   0.8957   0.0531
 -12.000  -0.0045   0.09986   0.09564  -0.1451   0.8930   0.0565
 -11.750  -0.0158   0.09417   0.08997  -0.1533   0.8900   0.0589
 -11.500  -0.0252   0.08832   0.08419  -0.1563   0.8868   0.0600
 -11.250  -0.0079   0.08663   0.08247  -0.1547   0.8837   0.0610
 -11.000   0.0049   0.08441   0.08023  -0.1549   0.8809   0.0623
 -10.750   0.0153   0.08194   0.07775  -0.1561   0.8781   0.0649
 -10.500   0.0194   0.07830   0.07409  -0.1590   0.8754   0.0661
  -8.000  -0.1911   0.03756   0.03164  -0.1503   0.8305   0.0360
  -7.750  -0.1921   0.03527   0.02906  -0.1467   0.8257   0.0338
  -7.500  -0.1855   0.03333   0.02680  -0.1440   0.8211   0.0335
  -7.250  -0.1690   0.03169   0.02487  -0.1427   0.8182   0.0336
  -7.000  -0.1473   0.03037   0.02332  -0.1421   0.8161   0.0348
  -6.750  -0.1238   0.02872   0.02138  -0.1415   0.8144   0.0345
  -6.500  -0.1226   0.02839   0.02100  -0.1373   0.8076   0.0346
  -6.250  -0.1018   0.02730   0.01976  -0.1361   0.8044   0.0351
  -6.000  -0.0767   0.02624   0.01858  -0.1356   0.8022   0.0363
  -5.750  -0.0503   0.02536   0.01759  -0.1353   0.8005   0.0378
  -5.500  -0.0408   0.02519   0.01740  -0.1324   0.7962   0.0387
  -5.250  -0.0377   0.02487   0.01718  -0.1288   0.7902   0.0424
  -5.000  -0.0148   0.02436   0.01662  -0.1282   0.7876   0.0470
  -4.750   0.0080   0.02338   0.01566  -0.1277   0.7858   0.0542
  -4.500   0.0327   0.02244   0.01472  -0.1275   0.7843   0.0749
  -4.250   0.0158   0.02329   0.01568  -0.1208   0.7749   0.0879
  -4.000   0.0256   0.02145   0.01492  -0.1192   0.7720   0.3002
  -3.750   0.0437   0.02074   0.01511  -0.1173   0.7703   0.5219
  -3.500   0.0342   0.02197   0.01638  -0.1114   0.7626   0.5528
  -3.250   0.0496   0.02265   0.01704  -0.1089   0.7584   0.5889
  -3.000   0.0782   0.02308   0.01735  -0.1085   0.7565   0.6166
  -2.750   0.1113   0.02334   0.01756  -0.1087   0.7553   0.6343
  -2.500   0.0822   0.02482   0.01908  -0.0997   0.7449   0.6379
  -2.250   0.1084   0.02519   0.01940  -0.0989   0.7425   0.6536
  -2.000   0.1381   0.02551   0.01969  -0.0986   0.7410   0.6698
  -1.750   0.1709   0.02573   0.01988  -0.0987   0.7400   0.6852
  -1.500   0.1314   0.02752   0.02170  -0.0886   0.7283   0.6899
  -1.250   0.1607   0.02755   0.02166  -0.0885   0.7266   0.6999
  -1.000   0.1927   0.02748   0.02150  -0.0890   0.7254   0.7086
  -0.750   0.1958   0.02833   0.02232  -0.0854   0.7200   0.7146
  -0.500   0.2485   0.02752   0.02141  -0.0889   0.7216   0.7209
  -0.250   0.2962   0.02697   0.02073  -0.0922   0.7224   0.7273
   0.000   0.3444   0.02642   0.02013  -0.0953   0.7229   0.7316
   0.250   0.2389   0.03061   0.02443  -0.0763   0.7002   0.7362
   0.500   0.2664   0.03063   0.02435  -0.0765   0.6978   0.7419
   0.750   0.2978   0.03044   0.02412  -0.0770   0.6964   0.7455
   1.000   0.3318   0.03018   0.02382  -0.0779   0.6953   0.7498
   1.250   0.3676   0.02988   0.02345  -0.0791   0.6945   0.7543
   1.500   0.4065   0.02942   0.02293  -0.0808   0.6939   0.7584
   1.750   0.3788   0.03147   0.02501  -0.0736   0.6815   0.7620
   2.000   0.4126   0.03124   0.02475  -0.0745   0.6804   0.7659
   2.250   0.4500   0.03082   0.02429  -0.0759   0.6797   0.7697
   2.500   0.4865   0.03050   0.02393  -0.0773   0.6791   0.7737
   2.750   0.4641   0.03254   0.02600  -0.0713   0.6666   0.7774
   3.000   0.4998   0.03219   0.02565  -0.0724   0.6657   0.7808
   3.250   0.5383   0.03166   0.02511  -0.0739   0.6650   0.7848
   3.500   0.5743   0.03130   0.02473  -0.0751   0.6641   0.7889
   3.750   0.5581   0.03337   0.02684  -0.0703   0.6517   0.7926
   4.000   0.5557   0.03504   0.02855  -0.0675   0.6418   0.7966
   4.250   0.5878   0.03488   0.02839  -0.0684   0.6393   0.8010
   4.500   0.6239   0.03447   0.02800  -0.0697   0.6379   0.8055
   4.750   0.6615   0.03403   0.02762  -0.0712   0.6369   0.8093
   5.000   0.7012   0.03342   0.02704  -0.0728   0.6362   0.8138
   5.250   0.7415   0.03267   0.02632  -0.0745   0.6357   0.8190
   5.500   0.7828   0.03188   0.02561  -0.0763   0.6352   0.8235
   5.750   0.8247   0.03099   0.02479  -0.0782   0.6349   0.8287
   6.250   0.8169   0.03546   0.02940  -0.0738   0.6098   0.8412
   6.500   0.8574   0.03471   0.02874  -0.0756   0.6089   0.8488
   6.750   0.9028   0.03371   0.02784  -0.0780   0.6084   0.8562
   7.000   0.9497   0.03240   0.02664  -0.0805   0.6081   0.8653
   7.250   1.0005   0.03100   0.02539  -0.0836   0.6081   0.8752
   7.500   1.0567   0.02930   0.02385  -0.0874   0.6082   0.8881
   7.750   1.1239   0.02717   0.02190  -0.0928   0.6085   0.9075
   8.000   1.2054   0.02472   0.01968  -0.1007   0.6085   0.9609
   8.250   1.2652   0.02274   0.01774  -0.1044   0.6068   1.0000
   8.500   1.2679   0.02375   0.01881  -0.1018   0.5960   1.0000
   8.750   1.3384   0.02125   0.01633  -0.1070   0.5911   1.0000
   9.000   1.3406   0.02196   0.01710  -0.1038   0.5787   1.0000
   9.250   1.3556   0.02197   0.01712  -0.1021   0.5642   1.0000
   9.500   1.3666   0.02244   0.01762  -0.1002   0.5497   1.0000
   9.750   1.3776   0.02301   0.01822  -0.0984   0.5341   1.0000
  10.000   1.3908   0.02357   0.01879  -0.0969   0.5179   1.0000
  10.250   1.4042   0.02418   0.01940  -0.0954   0.5009   1.0000
  10.500   1.4084   0.02540   0.02062  -0.0931   0.4803   1.0000
  10.750   1.4158   0.02644   0.02160  -0.0911   0.4575   1.0000
  11.000   1.4189   0.02783   0.02293  -0.0888   0.4322   1.0000
  11.250   1.4197   0.02940   0.02440  -0.0863   0.4045   1.0000
  11.500   1.4159   0.03136   0.02622  -0.0836   0.3741   1.0000
  11.750   1.4090   0.03368   0.02838  -0.0807   0.3422   1.0000
  12.000   1.4007   0.03626   0.03080  -0.0781   0.3104   1.0000
  12.250   1.3909   0.03915   0.03351  -0.0755   0.2783   1.0000
  12.500   1.3785   0.04240   0.03657  -0.0731   0.2448   1.0000
  12.750   1.3668   0.04577   0.03976  -0.0709   0.2117   1.0000
  13.000   1.3544   0.04935   0.04313  -0.0689   0.1782   1.0000
  13.250   1.3410   0.05315   0.04671  -0.0671   0.1455   1.0000
  13.500   1.3274   0.05711   0.05046  -0.0654   0.1161   1.0000
  13.750   1.3163   0.06092   0.05409  -0.0640   0.0924   1.0000
  14.000   1.3074   0.06462   0.05767  -0.0628   0.0779   1.0000
  14.250   1.3020   0.06805   0.06107  -0.0619   0.0672   1.0000
  14.500   1.3002   0.07114   0.06421  -0.0611   0.0601   1.0000
  14.750   1.2930   0.07483   0.06783  -0.0603   0.0547   1.0000
  15.000   1.2964   0.07743   0.07055  -0.0599   0.0493   1.0000
  15.250   1.2930   0.08075   0.07387  -0.0593   0.0459   1.0000
  15.500   1.2928   0.08374   0.07694  -0.0587   0.0419   1.0000
  15.750   1.2944   0.08658   0.07984  -0.0584   0.0389   1.0000
  16.000   1.2918   0.08952   0.08269  -0.0575   0.0357   1.0000
  16.250   1.2961   0.09216   0.08551  -0.0574   0.0333   1.0000
  16.500   1.2990   0.09490   0.08831  -0.0574   0.0310   1.0000
  16.750   1.3020   0.09703   0.09036  -0.0564   0.0286   1.0000
  17.000   1.3070   0.09946   0.09294  -0.0562   0.0270   1.0000
  17.250   1.3112   0.10204   0.09565  -0.0561   0.0253   1.0000
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