Airfoil Tools
Search 1636 airfoils Google+
You have 0 airfoils loaded.
Your Reynold number range is 50,000 to 1,000,000. (set)

74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 200,000
Max Cl/Cd: 78.88 at α=6.5°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-200000-n5.txt
Download as CSV file: xf-fx74130wp2mod-il-200000-n5.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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1635   0.09201   0.08772  -0.0972   0.8478   0.0250
  -9.750  -0.1622   0.08853   0.08428  -0.1000   0.8459   0.0263
  -9.500  -0.1600   0.08521   0.08099  -0.1024   0.8437   0.0266
  -9.250  -0.1598   0.08151   0.07732  -0.1055   0.8412   0.0271
  -9.000  -0.1594   0.07758   0.07341  -0.1084   0.8386   0.0272
  -8.750  -0.1612   0.07329   0.06913  -0.1121   0.8363   0.0272
  -8.500  -0.1656   0.06954   0.06534  -0.1144   0.8340   0.0273
  -8.250  -0.1740   0.06649   0.06225  -0.1148   0.8313   0.0273
  -8.000  -0.1796   0.06351   0.05921  -0.1148   0.8285   0.0273
  -7.750  -0.1809   0.06050   0.05609  -0.1148   0.8259   0.0274
  -7.500  -0.1795   0.05753   0.05299  -0.1145   0.8234   0.0274
  -7.250  -0.1844   0.05014   0.04554  -0.1139   0.8212   0.0176
  -7.000  -0.1819   0.04698   0.04224  -0.1132   0.8186   0.0167
  -6.750  -0.1767   0.04375   0.03882  -0.1123   0.8147   0.0158
  -6.500  -0.1690   0.04015   0.03495  -0.1112   0.8112   0.0148
  -6.250  -0.1596   0.03559   0.02994  -0.1094   0.8084   0.0135
  -6.000  -0.1438   0.03165   0.02538  -0.1074   0.8063   0.0124
  -5.500  -0.1061   0.02766   0.02073  -0.1055   0.8009   0.0121
  -5.250  -0.0857   0.02549   0.01822  -0.1046   0.7984   0.0122
  -5.000  -0.0637   0.02332   0.01569  -0.1038   0.7961   0.0123
  -4.750  -0.0398   0.02161   0.01371  -0.1033   0.7941   0.0127
  -4.500  -0.0147   0.02037   0.01228  -0.1029   0.7923   0.0132
  -4.250   0.0095   0.01979   0.01161  -0.1026   0.7897   0.0148
  -4.000   0.0340   0.01916   0.01087  -0.1022   0.7868   0.0164
  -3.750   0.0587   0.01825   0.00987  -0.1017   0.7842   0.0170
  -3.500   0.0834   0.01744   0.00897  -0.1011   0.7819   0.0175
  -3.250   0.1084   0.01676   0.00820  -0.1007   0.7798   0.0181
  -3.000   0.1333   0.01608   0.00741  -0.1003   0.7779   0.0191
  -2.750   0.1560   0.01564   0.00695  -0.0997   0.7741   0.0215
  -2.500   0.1810   0.01532   0.00655  -0.0993   0.7710   0.0260
  -2.250   0.2060   0.01480   0.00614  -0.0990   0.7684   0.0574
  -2.000   0.2258   0.01328   0.00581  -0.0989   0.7661   0.3695
  -1.750   0.2342   0.01252   0.00648  -0.0940   0.7639   0.7674
  -1.500   0.2534   0.01291   0.00684  -0.0918   0.7594   0.8152
  -1.250   0.2680   0.01323   0.00717  -0.0879   0.7558   0.8498
  -1.000   0.2848   0.01337   0.00725  -0.0846   0.7531   0.8706
  -0.750   0.3084   0.01335   0.00713  -0.0833   0.7511   0.8802
  -0.500   0.3304   0.01341   0.00713  -0.0824   0.7468   0.8872
  -0.250   0.3546   0.01341   0.00706  -0.0818   0.7429   0.8913
   0.000   0.3810   0.01335   0.00693  -0.0816   0.7400   0.8945
   0.250   0.4092   0.01326   0.00675  -0.0818   0.7377   0.8975
   0.500   0.4336   0.01329   0.00675  -0.0815   0.7331   0.9007
   0.750   0.4593   0.01328   0.00671  -0.0814   0.7288   0.9033
   1.000   0.4865   0.01321   0.00659  -0.0815   0.7258   0.9053
   1.250   0.5152   0.01312   0.00646  -0.0818   0.7235   0.9072
   1.500   0.5377   0.01322   0.00658  -0.0812   0.7178   0.9097
   1.750   0.5644   0.01320   0.00656  -0.0813   0.7139   0.9117
   2.000   0.5931   0.01313   0.00646  -0.0817   0.7110   0.9137
   2.250   0.6188   0.01318   0.00654  -0.0817   0.7063   0.9157
   2.500   0.6441   0.01320   0.00659  -0.0816   0.7013   0.9175
   2.750   0.6718   0.01314   0.00653  -0.0818   0.6980   0.9193
   3.000   0.6980   0.01315   0.00658  -0.0817   0.6941   0.9212
   3.250   0.7222   0.01324   0.00674  -0.0815   0.6888   0.9232
   3.500   0.7502   0.01322   0.00675  -0.0818   0.6852   0.9249
   3.750   0.7780   0.01321   0.00677  -0.0821   0.6816   0.9270
   4.000   0.8016   0.01334   0.00698  -0.0817   0.6758   0.9298
   4.250   0.8290   0.01334   0.00707  -0.0819   0.6721   0.9316
   4.500   0.8580   0.01331   0.00708  -0.0824   0.6690   0.9333
   4.750   0.8805   0.01347   0.00735  -0.0818   0.6628   0.9359
   5.000   0.9087   0.01344   0.00738  -0.0821   0.6580   0.9381
   5.250   0.9338   0.01345   0.00750  -0.0818   0.6500   0.9410
   5.500   0.9611   0.01329   0.00738  -0.0817   0.6389   0.9440
   5.750   0.9860   0.01318   0.00729  -0.0812   0.6236   0.9472
   6.000   1.0107   0.01315   0.00729  -0.0807   0.6072   0.9507
   6.250   1.0350   0.01320   0.00730  -0.0801   0.5878   0.9548
   6.500   1.0562   0.01339   0.00753  -0.0791   0.5651   0.9603
   6.750   1.0766   0.01366   0.00778  -0.0781   0.5359   0.9684
   7.250   1.0982   0.01475   0.00858  -0.0732   0.4346   1.0000
   7.500   1.0869   0.01616   0.00955  -0.0676   0.3617   1.0000
   7.750   1.0781   0.01789   0.01093  -0.0632   0.3011   1.0000
   8.000   1.0733   0.01967   0.01242  -0.0597   0.2462   1.0000
   8.250   1.0708   0.02149   0.01396  -0.0568   0.1944   1.0000
   8.500   1.0703   0.02328   0.01552  -0.0542   0.1467   1.0000
   8.750   1.0722   0.02501   0.01702  -0.0520   0.1070   1.0000
   9.000   1.0763   0.02663   0.01849  -0.0501   0.0777   1.0000
   9.250   1.0826   0.02815   0.01992  -0.0484   0.0577   1.0000
   9.500   1.0897   0.02966   0.02137  -0.0468   0.0449   1.0000
   9.750   1.0986   0.03106   0.02280  -0.0454   0.0363   1.0000
  10.000   1.1071   0.03252   0.02429  -0.0441   0.0296   1.0000
  10.250   1.1148   0.03407   0.02585  -0.0428   0.0237   1.0000
  10.500   1.1239   0.03555   0.02743  -0.0416   0.0203   1.0000
  10.750   1.1316   0.03718   0.02913  -0.0403   0.0173   1.0000
  11.000   1.1350   0.03924   0.03129  -0.0388   0.0149   1.0000
  11.250   1.1446   0.04080   0.03298  -0.0379   0.0130   1.0000
  11.500   1.1543   0.04237   0.03462  -0.0370   0.0110   1.0000
  11.750   1.1584   0.04452   0.03685  -0.0359   0.0100   1.0000
  12.000   1.1628   0.04674   0.03919  -0.0348   0.0094   1.0000
  12.250   1.1697   0.04877   0.04138  -0.0338   0.0089   1.0000
  12.500   1.1765   0.05088   0.04363  -0.0329   0.0084   1.0000
  12.750   1.1837   0.05302   0.04591  -0.0320   0.0081   1.0000
  13.000   1.1911   0.05521   0.04825  -0.0312   0.0077   1.0000
  13.250   1.1983   0.05749   0.05068  -0.0305   0.0074   1.0000
  13.500   1.2049   0.05989   0.05324  -0.0299   0.0071   1.0000
  13.750   1.2103   0.06246   0.05597  -0.0294   0.0069   1.0000
  14.000   1.2149   0.06523   0.05896  -0.0290   0.0067   1.0000
  14.250   1.2176   0.06826   0.06218  -0.0286   0.0066   1.0000
  14.500   1.2181   0.07161   0.06573  -0.0284   0.0065   1.0000
  14.750   1.2167   0.07534   0.06968  -0.0284   0.0064   1.0000
  15.000   1.2119   0.07962   0.07418  -0.0287   0.0063   1.0000
  15.250   1.2062   0.08408   0.07888  -0.0292   0.0063   1.0000
  15.500   1.1968   0.08922   0.08427  -0.0301   0.0062   1.0000
  15.750   1.1863   0.09465   0.08995  -0.0315   0.0062   1.0000
  16.000   1.1735   0.10067   0.09621  -0.0335   0.0062   1.0000
  16.250   1.1590   0.10718   0.10294  -0.0360   0.0061   1.0000
  16.500   1.1445   0.11399   0.10998  -0.0391   0.0061   1.0000
  16.750   1.1298   0.12122   0.11742  -0.0428   0.0061   1.0000
  17.000   1.1145   0.12899   0.12540  -0.0471   0.0062   1.0000
  17.250   1.0993   0.13739   0.13400  -0.0522   0.0062   1.0000
  17.500   1.0813   0.14729   0.14412  -0.0586   0.0063   1.0000
<< Back to 74-130 WP2 MOD (fx74130wp2mod-il)

Polar data table (+)

Polar graphs


<< Back to 74-130 WP2 MOD (fx74130wp2mod-il)