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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 1,000,000
Max Cl/Cd: 141.16 at α=4.75°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-1000000.txt
Download as CSV file: xf-fx74130wp2mod-il-1000000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: 74-130 WP2 MOD                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     1.000 e 6     Ncrit =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1707   0.08181   0.07921  -0.1023   0.8016   0.0082
  -9.750  -0.1669   0.07899   0.07640  -0.1036   0.8003   0.0084
  -9.500  -0.1659   0.07456   0.07199  -0.1060   0.7986   0.0081
  -9.250  -0.1653   0.07165   0.06909  -0.1074   0.7970   0.0084
  -9.000  -0.1638   0.06857   0.06602  -0.1091   0.7951   0.0086
  -8.750  -0.1676   0.06438   0.06184  -0.1121   0.7928   0.0087
  -8.500  -0.1814   0.05926   0.05673  -0.1160   0.7905   0.0087
  -8.250  -0.1950   0.05625   0.05371  -0.1157   0.7882   0.0088
  -8.000  -0.2028   0.05237   0.04976  -0.1159   0.7858   0.0088
  -7.750  -0.2013   0.04960   0.04692  -0.1157   0.7838   0.0090
  -7.500  -0.1989   0.04635   0.04356  -0.1154   0.7823   0.0091
  -7.250  -0.1934   0.04326   0.04035  -0.1149   0.7808   0.0095
  -7.000  -0.1855   0.04014   0.03708  -0.1141   0.7792   0.0098
  -6.750  -0.1754   0.03699   0.03375  -0.1132   0.7777   0.0103
  -6.500  -0.1587   0.03408   0.03066  -0.1120   0.7765   0.0114
  -6.250  -0.1361   0.03263   0.02904  -0.1111   0.7752   0.0120
  -6.000  -0.1206   0.03022   0.02641  -0.1100   0.7738   0.0121
  -5.750  -0.1044   0.02778   0.02373  -0.1089   0.7723   0.0121
  -5.500  -0.0860   0.02565   0.02136  -0.1080   0.7708   0.0121
  -4.250   0.0223   0.01296   0.00733  -0.1039   0.7633   0.0097
  -4.000   0.0469   0.01141   0.00562  -0.1030   0.7619   0.0090
  -3.750   0.0726   0.01076   0.00492  -0.1028   0.7603   0.0094
  -3.500   0.0990   0.01030   0.00443  -0.1027   0.7585   0.0102
  -3.250   0.1257   0.00989   0.00398  -0.1026   0.7567   0.0109
  -3.000   0.1528   0.00955   0.00359  -0.1027   0.7550   0.0115
  -2.750   0.1801   0.00925   0.00323  -0.1028   0.7532   0.0118
  -2.500   0.2075   0.00896   0.00287  -0.1029   0.7514   0.0127
  -2.250   0.2349   0.00867   0.00253  -0.1029   0.7494   0.0145
  -2.000   0.2623   0.00835   0.00226  -0.1030   0.7473   0.0322
  -1.750   0.2876   0.00757   0.00208  -0.1032   0.7450   0.2193
  -1.250   0.3374   0.00584   0.00200  -0.1035   0.7406   0.7674
  -1.000   0.3655   0.00596   0.00209  -0.1035   0.7385   0.7950
  -0.750   0.3934   0.00609   0.00220  -0.1035   0.7361   0.8090
  -0.500   0.4208   0.00618   0.00231  -0.1033   0.7335   0.8211
  -0.250   0.4478   0.00624   0.00239  -0.1031   0.7305   0.8297
   0.000   0.4757   0.00625   0.00238  -0.1031   0.7275   0.8357
   0.250   0.5033   0.00627   0.00238  -0.1031   0.7247   0.8403
   0.500   0.5315   0.00631   0.00240  -0.1033   0.7215   0.8449
   0.750   0.5595   0.00628   0.00239  -0.1035   0.7176   0.8484
   1.000   0.5873   0.00625   0.00235  -0.1036   0.7138   0.8508
   1.250   0.6155   0.00624   0.00232  -0.1039   0.7103   0.8527
   1.500   0.6438   0.00623   0.00232  -0.1042   0.7057   0.8544
   1.750   0.6723   0.00621   0.00231  -0.1046   0.7006   0.8559
   2.000   0.7007   0.00621   0.00228  -0.1049   0.6960   0.8573
   2.250   0.7292   0.00621   0.00230  -0.1053   0.6896   0.8585
   2.500   0.7575   0.00622   0.00228  -0.1057   0.6834   0.8594
   2.750   0.7859   0.00624   0.00232  -0.1061   0.6759   0.8603
   3.000   0.8136   0.00627   0.00232  -0.1063   0.6682   0.8612
   3.250   0.8410   0.00629   0.00234  -0.1065   0.6588   0.8620
   3.500   0.8678   0.00635   0.00237  -0.1065   0.6473   0.8630
   3.750   0.8937   0.00645   0.00245  -0.1064   0.6333   0.8640
   4.000   0.9192   0.00658   0.00254  -0.1062   0.6188   0.8650
   4.250   0.9444   0.00674   0.00265  -0.1059   0.6035   0.8658
   4.500   0.9700   0.00689   0.00277  -0.1058   0.5903   0.8667
   4.750   0.9952   0.00705   0.00292  -0.1056   0.5763   0.8677
   5.000   1.0193   0.00727   0.00308  -0.1051   0.5591   0.8688
   5.250   1.0444   0.00743   0.00324  -0.1049   0.5456   0.8700
   5.500   1.0697   0.00759   0.00340  -0.1048   0.5327   0.8710
   5.750   1.0936   0.00781   0.00359  -0.1043   0.5141   0.8720
   6.000   1.1149   0.00814   0.00384  -0.1034   0.4826   0.8731
   6.250   1.1203   0.00919   0.00443  -0.0997   0.3879   0.8745
   6.500   1.1166   0.01055   0.00527  -0.0945   0.2901   0.8766
   6.750   1.1182   0.01145   0.00590  -0.0901   0.2305   0.8787
   7.000   1.1114   0.01254   0.00666  -0.0843   0.1695   0.8816
   7.250   1.1095   0.01358   0.00747  -0.0797   0.1217   0.8844
   7.500   1.1127   0.01456   0.00828  -0.0762   0.0882   0.8868
   7.750   1.1183   0.01553   0.00912  -0.0733   0.0609   0.8891
   8.000   1.1267   0.01640   0.00994  -0.0709   0.0441   0.8917
   8.250   1.1379   0.01718   0.01070  -0.0690   0.0337   0.8944
   8.500   1.1507   0.01791   0.01143  -0.0673   0.0272   0.8972
   8.750   1.1639   0.01866   0.01220  -0.0658   0.0219   0.9001
   9.000   1.1767   0.01946   0.01299  -0.0643   0.0180   0.9033
   9.250   1.1886   0.02026   0.01383  -0.0626   0.0132   0.9077
   9.500   1.1962   0.02137   0.01494  -0.0604   0.0077   0.9134
   9.750   1.2026   0.02258   0.01623  -0.0580   0.0060   0.9209
  10.000   1.2133   0.02345   0.01720  -0.0562   0.0055   0.9328
  10.250   1.2267   0.02441   0.01833  -0.0552   0.0051   0.9735
  10.500   1.2396   0.02537   0.01934  -0.0542   0.0047   1.0000
  10.750   1.2509   0.02652   0.02054  -0.0529   0.0045   1.0000
  11.000   1.2608   0.02778   0.02186  -0.0516   0.0042   1.0000
  11.250   1.2685   0.02924   0.02340  -0.0501   0.0040   1.0000
  11.500   1.2711   0.03113   0.02540  -0.0481   0.0038   1.0000
  11.750   1.2720   0.03324   0.02764  -0.0461   0.0037   1.0000
  12.000   1.2756   0.03519   0.02970  -0.0445   0.0037   1.0000
  12.250   1.2820   0.03697   0.03156  -0.0431   0.0036   1.0000
  12.500   1.2906   0.03858   0.03326  -0.0421   0.0036   1.0000
  12.750   1.2989   0.04026   0.03503  -0.0412   0.0035   1.0000
  13.000   1.3069   0.04201   0.03688  -0.0402   0.0035   1.0000
  13.250   1.3123   0.04408   0.03907  -0.0392   0.0034   1.0000
  13.500   1.3201   0.04596   0.04105  -0.0384   0.0034   1.0000
  13.750   1.3251   0.04819   0.04340  -0.0375   0.0033   1.0000
  14.000   1.3310   0.05034   0.04566  -0.0369   0.0032   1.0000
  14.250   1.3355   0.05274   0.04819  -0.0362   0.0031   1.0000
  14.500   1.3383   0.05541   0.05099  -0.0356   0.0030   1.0000
  14.750   1.3405   0.05821   0.05393  -0.0352   0.0030   1.0000
  15.000   1.3412   0.06125   0.05711  -0.0349   0.0028   1.0000
  15.250   1.3401   0.06464   0.06065  -0.0347   0.0028   1.0000
  15.500   1.3379   0.06826   0.06442  -0.0347   0.0027   1.0000
  15.750   1.3328   0.07238   0.06872  -0.0349   0.0027   1.0000
  16.000   1.3259   0.07690   0.07342  -0.0354   0.0027   1.0000
  16.250   1.3175   0.08181   0.07850  -0.0363   0.0027   1.0000
  16.500   1.3067   0.08727   0.08415  -0.0375   0.0026   1.0000
  16.750   1.2914   0.09368   0.09077  -0.0392   0.0027   1.0000
  17.000   1.2768   0.10021   0.09749  -0.0415   0.0026   1.0000
  17.250   1.2574   0.10796   0.10545  -0.0446   0.0027   1.0000
  17.500   1.2366   0.11638   0.11407  -0.0484   0.0027   1.0000
  17.750   1.2147   0.12550   0.12340  -0.0531   0.0027   1.0000
  18.000   1.1922   0.13542   0.13350  -0.0588   0.0028   1.0000
  18.250   1.1697   0.14602   0.14429  -0.0652   0.0028   1.0000
  18.500   1.1481   0.15715   0.15558  -0.0723   0.0029   1.0000
  18.750   1.1230   0.17024   0.16882  -0.0805   0.0029   1.0000
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