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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 150.77 at α=4.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-1000000-n5.txt
Download as CSV file: xf-fx74130wp2-il-1000000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2                                      
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.250  -0.1809   0.08604   0.08305  -0.0970   0.7293   0.0044
 -10.000  -0.1825   0.08112   0.07815  -0.0993   0.7285   0.0048
  -6.500  -0.1977   0.02236   0.01788  -0.1055   0.7156   0.0046
  -6.250  -0.1831   0.01863   0.01367  -0.1038   0.7148   0.0045
  -6.000  -0.1622   0.01644   0.01114  -0.1029   0.7139   0.0045
  -5.750  -0.1388   0.01496   0.00939  -0.1025   0.7130   0.0045
  -5.500  -0.1141   0.01382   0.00806  -0.1021   0.7122   0.0046
  -5.250  -0.0887   0.01299   0.00708  -0.1019   0.7114   0.0046
  -5.000  -0.0628   0.01234   0.00632  -0.1018   0.7107   0.0047
  -4.750  -0.0382   0.01142   0.00527  -0.1014   0.7099   0.0049
  -4.500  -0.0131   0.01074   0.00450  -0.1012   0.7091   0.0054
  -4.250   0.0137   0.01041   0.00413  -0.1013   0.7084   0.0057
  -4.000   0.0408   0.01012   0.00382  -0.1014   0.7078   0.0061
  -3.750   0.0679   0.00984   0.00352  -0.1016   0.7071   0.0065
  -3.500   0.0951   0.00956   0.00320  -0.1017   0.7063   0.0067
  -3.250   0.1226   0.00932   0.00294  -0.1019   0.7054   0.0070
  -3.000   0.1503   0.00912   0.00270  -0.1021   0.7045   0.0074
  -2.750   0.1783   0.00898   0.00256  -0.1024   0.7037   0.0078
  -2.500   0.2060   0.00874   0.00227  -0.1026   0.7029   0.0086
  -2.250   0.2341   0.00858   0.00210  -0.1028   0.7021   0.0096
  -2.000   0.2622   0.00844   0.00196  -0.1031   0.7013   0.0140
  -1.750   0.2902   0.00826   0.00186  -0.1035   0.7005   0.0348
  -1.500   0.3181   0.00805   0.00177  -0.1038   0.6996   0.0759
  -1.250   0.3447   0.00749   0.00168  -0.1042   0.6987   0.2347
  -1.000   0.3704   0.00652   0.00156  -0.1049   0.6978   0.5188
  -0.750   0.3966   0.00590   0.00164  -0.1051   0.6971   0.7502
  -0.500   0.4251   0.00598   0.00174  -0.1053   0.6963   0.7808
  -0.250   0.4538   0.00607   0.00180  -0.1056   0.6955   0.7935
   0.000   0.4825   0.00613   0.00186  -0.1060   0.6946   0.8015
   0.250   0.5112   0.00618   0.00190  -0.1063   0.6938   0.8072
   0.500   0.5396   0.00622   0.00196  -0.1066   0.6928   0.8121
   0.750   0.5684   0.00627   0.00201  -0.1070   0.6919   0.8163
   1.000   0.5975   0.00631   0.00204  -0.1075   0.6910   0.8189
   1.250   0.6262   0.00632   0.00207  -0.1079   0.6899   0.8205
   1.500   0.6550   0.00634   0.00209  -0.1084   0.6886   0.8216
   1.750   0.6838   0.00634   0.00211  -0.1088   0.6870   0.8226
   2.000   0.7125   0.00634   0.00211  -0.1092   0.6851   0.8234
   2.250   0.7412   0.00635   0.00210  -0.1096   0.6828   0.8242
   2.500   0.7698   0.00636   0.00214  -0.1100   0.6802   0.8252
   2.750   0.7982   0.00635   0.00217  -0.1104   0.6767   0.8261
   3.000   0.8266   0.00633   0.00217  -0.1108   0.6728   0.8269
   3.250   0.8549   0.00633   0.00217  -0.1111   0.6688   0.8276
   3.500   0.8832   0.00633   0.00221  -0.1115   0.6634   0.8284
   3.750   0.9111   0.00633   0.00223  -0.1117   0.6563   0.8293
   4.000   0.9387   0.00634   0.00226  -0.1119   0.6456   0.8303
   4.250   0.9649   0.00640   0.00228  -0.1118   0.6263   0.8312
   4.500   0.9894   0.00657   0.00236  -0.1114   0.5977   0.8320
   4.750   0.9989   0.00754   0.00286  -0.1083   0.5016   0.8330
   5.000   1.0026   0.00880   0.00362  -0.1043   0.3997   0.8343
   5.250   1.0125   0.00965   0.00418  -0.1014   0.3365   0.8355
   5.500   1.0221   0.01043   0.00472  -0.0985   0.2821   0.8368
   5.750   1.0329   0.01108   0.00520  -0.0958   0.2417   0.8382
   6.000   1.0383   0.01172   0.00569  -0.0920   0.2045   0.8399
   6.250   1.0397   0.01250   0.00631  -0.0876   0.1675   0.8417
   6.500   1.0436   0.01330   0.00698  -0.0840   0.1371   0.8434
   6.750   1.0499   0.01412   0.00770  -0.0810   0.1126   0.8450
   7.000   1.0545   0.01514   0.00858  -0.0780   0.0830   0.8465
   7.250   1.0625   0.01608   0.00942  -0.0756   0.0602   0.8480
   7.500   1.0706   0.01705   0.01030  -0.0733   0.0393   0.8496
   7.750   1.0832   0.01783   0.01105  -0.0717   0.0292   0.8511
   8.000   1.0971   0.01857   0.01177  -0.0703   0.0230   0.8527
   8.250   1.1122   0.01924   0.01247  -0.0690   0.0194   0.8544
   8.500   1.1266   0.01998   0.01321  -0.0677   0.0157   0.8563
   8.750   1.1426   0.02063   0.01390  -0.0667   0.0141   0.8581
   9.000   1.1561   0.02146   0.01471  -0.0654   0.0103   0.8598
   9.500   1.1837   0.02309   0.01637  -0.0629   0.0055   0.8632
   9.750   1.1968   0.02396   0.01727  -0.0615   0.0041   0.8653
  10.000   1.2104   0.02482   0.01820  -0.0603   0.0036   0.8675
  10.250   1.2242   0.02568   0.01911  -0.0592   0.0032   0.8699
  10.500   1.2378   0.02658   0.02006  -0.0580   0.0029   0.8724
  10.750   1.2511   0.02750   0.02103  -0.0569   0.0027   0.8748
  11.000   1.2629   0.02853   0.02212  -0.0557   0.0024   0.8778
  11.250   1.2741   0.02962   0.02330  -0.0544   0.0021   0.8813
  11.500   1.2851   0.03076   0.02452  -0.0531   0.0021   0.8852
  12.000   1.3063   0.03314   0.02708  -0.0506   0.0020   0.8951
  12.250   1.3162   0.03442   0.02846  -0.0494   0.0019   0.9024
  12.500   1.3269   0.03551   0.02968  -0.0482   0.0019   0.9152
  12.750   1.3382   0.03678   0.03114  -0.0474   0.0019   0.9667
  13.250   1.3575   0.03964   0.03415  -0.0454   0.0018   1.0000
  13.500   1.3661   0.04125   0.03585  -0.0445   0.0018   1.0000
  13.750   1.3747   0.04290   0.03758  -0.0437   0.0017   1.0000
  14.000   1.3815   0.04477   0.03955  -0.0428   0.0017   1.0000
  14.250   1.3892   0.04659   0.04146  -0.0421   0.0016   1.0000
  14.500   1.3963   0.04849   0.04345  -0.0414   0.0016   1.0000
  14.750   1.4011   0.05069   0.04576  -0.0406   0.0016   1.0000
  15.000   1.4051   0.05303   0.04821  -0.0400   0.0016   1.0000
  15.250   1.4099   0.05535   0.05063  -0.0395   0.0015   1.0000
  15.500   1.4127   0.05794   0.05336  -0.0390   0.0015   1.0000
  15.750   1.4157   0.06057   0.05610  -0.0387   0.0014   1.0000
  16.000   1.4176   0.06340   0.05905  -0.0385   0.0014   1.0000
  16.250   1.4195   0.06632   0.06207  -0.0384   0.0013   1.0000
  16.500   1.4175   0.06984   0.06573  -0.0384   0.0013   1.0000
  16.750   1.4179   0.07311   0.06912  -0.0387   0.0013   1.0000
  17.000   1.4167   0.07671   0.07283  -0.0392   0.0013   1.0000
  17.250   1.4131   0.08076   0.07701  -0.0398   0.0012   1.0000
  17.500   1.4076   0.08524   0.08164  -0.0408   0.0012   1.0000
  17.750   1.4006   0.09010   0.08665  -0.0420   0.0012   1.0000
  18.000   1.3943   0.09499   0.09167  -0.0435   0.0012   1.0000
  18.250   1.3863   0.10032   0.09713  -0.0454   0.0012   1.0000
  18.500   1.3759   0.10625   0.10322  -0.0478   0.0012   1.0000
  18.750   1.3640   0.11266   0.10978  -0.0506   0.0012   1.0000
  19.000   1.3529   0.11911   0.11637  -0.0537   0.0012   1.0000
  19.250   1.3395   0.12617   0.12358  -0.0573   0.0011   1.0000
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