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74-130 WP2 (fx74130wp2-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 (fx74130wp2-il)
Reynolds number: 1,000,000
Max Cl/Cd: 161.37 at α=5.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2-il-1000000.txt
Download as CSV file: xf-fx74130wp2-il-1000000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1567   0.08528   0.08240  -0.1009   0.7529   0.0077
  -9.750  -0.1679   0.07965   0.07681  -0.1029   0.7520   0.0082
  -9.500  -0.1647   0.07660   0.07376  -0.1044   0.7509   0.0084
  -9.250  -0.1656   0.07249   0.06966  -0.1067   0.7497   0.0083
  -9.000  -0.1622   0.06988   0.06708  -0.1081   0.7490   0.0086
  -8.750  -0.1634   0.06627   0.06351  -0.1104   0.7481   0.0088
  -8.500  -0.1784   0.06049   0.05776  -0.1152   0.7470   0.0086
  -8.250  -0.1936   0.05703   0.05429  -0.1154   0.7458   0.0087
  -8.000  -0.1992   0.05379   0.05101  -0.1156   0.7447   0.0088
  -7.750  -0.2010   0.05031   0.04745  -0.1156   0.7437   0.0089
  -7.500  -0.1979   0.04727   0.04432  -0.1154   0.7426   0.0092
  -7.250  -0.1928   0.04406   0.04100  -0.1149   0.7417   0.0094
  -7.000  -0.1851   0.04085   0.03764  -0.1143   0.7406   0.0097
  -6.750  -0.1750   0.03761   0.03423  -0.1134   0.7396   0.0102
  -6.500  -0.1579   0.03470   0.03111  -0.1123   0.7387   0.0113
  -6.250  -0.1356   0.03320   0.02942  -0.1115   0.7378   0.0119
  -6.000  -0.1204   0.03075   0.02674  -0.1104   0.7368   0.0119
  -5.750  -0.1037   0.02849   0.02425  -0.1094   0.7359   0.0120
  -5.500  -0.0858   0.02617   0.02169  -0.1084   0.7353   0.0120
  -4.250   0.0226   0.01337   0.00760  -0.1045   0.7311   0.0096
  -4.000   0.0476   0.01195   0.00603  -0.1038   0.7302   0.0092
  -3.750   0.0737   0.01136   0.00539  -0.1036   0.7294   0.0097
  -3.500   0.1001   0.01089   0.00488  -0.1036   0.7285   0.0103
  -3.250   0.1269   0.01052   0.00447  -0.1036   0.7277   0.0110
  -3.000   0.1539   0.01018   0.00408  -0.1037   0.7270   0.0114
  -2.750   0.1814   0.00992   0.00378  -0.1038   0.7261   0.0118
  -2.500   0.2086   0.00956   0.00335  -0.1039   0.7253   0.0128
  -2.250   0.2364   0.00933   0.00305  -0.1041   0.7244   0.0141
  -2.000   0.2642   0.00908   0.00282  -0.1043   0.7236   0.0314
  -1.750   0.2899   0.00846   0.00275  -0.1046   0.7226   0.2052
  -1.500   0.3150   0.00758   0.00265  -0.1051   0.7219   0.4600
  -1.250   0.3396   0.00676   0.00277  -0.1050   0.7212   0.7638
  -1.000   0.3675   0.00690   0.00293  -0.1051   0.7203   0.7945
  -0.750   0.3953   0.00702   0.00306  -0.1051   0.7194   0.8088
  -0.500   0.4227   0.00716   0.00320  -0.1050   0.7184   0.8213
  -0.250   0.4500   0.00728   0.00334  -0.1048   0.7174   0.8299
   0.000   0.4778   0.00735   0.00341  -0.1049   0.7165   0.8359
   0.250   0.5053   0.00742   0.00349  -0.1050   0.7155   0.8408
   0.500   0.5339   0.00749   0.00355  -0.1053   0.7145   0.8453
   0.750   0.5623   0.00752   0.00357  -0.1056   0.7136   0.8487
   1.000   0.5905   0.00754   0.00360  -0.1058   0.7127   0.8510
   1.250   0.6192   0.00757   0.00361  -0.1062   0.7117   0.8529
   1.500   0.6483   0.00758   0.00361  -0.1067   0.7104   0.8545
   1.750   0.6773   0.00767   0.00369  -0.1072   0.7086   0.8560
   2.000   0.7058   0.00763   0.00368  -0.1077   0.7071   0.8574
   2.250   0.7344   0.00761   0.00368  -0.1081   0.7052   0.8586
   2.500   0.7632   0.00757   0.00365  -0.1086   0.7030   0.8596
   2.750   0.7925   0.00750   0.00359  -0.1091   0.7005   0.8605
   3.000   0.8221   0.00741   0.00350  -0.1097   0.6981   0.8612
   3.250   0.8513   0.00737   0.00344  -0.1102   0.6955   0.8620
   3.500   0.8789   0.00728   0.00341  -0.1104   0.6922   0.8629
   3.750   0.9070   0.00715   0.00334  -0.1107   0.6880   0.8639
   4.000   0.9357   0.00701   0.00320  -0.1110   0.6835   0.8648
   4.250   0.9632   0.00691   0.00314  -0.1112   0.6772   0.8656
   4.500   0.9911   0.00682   0.00309  -0.1114   0.6714   0.8664
   4.750   1.0184   0.00673   0.00304  -0.1115   0.6609   0.8673
   5.000   1.0456   0.00669   0.00303  -0.1116   0.6497   0.8682
   5.250   1.0723   0.00670   0.00306  -0.1116   0.6362   0.8693
   5.500   1.0973   0.00680   0.00311  -0.1113   0.6130   0.8705
   5.750   1.1118   0.00738   0.00341  -0.1090   0.5427   0.8719
   6.000   1.1168   0.00851   0.00410  -0.1051   0.4556   0.8734
   6.250   1.1196   0.00964   0.00484  -0.1010   0.3757   0.8749
   6.500   1.1169   0.01077   0.00559  -0.0959   0.2993   0.8771
   6.750   1.1085   0.01175   0.00630  -0.0897   0.2418   0.8797
   7.000   1.0995   0.01290   0.00719  -0.0837   0.1902   0.8829
   7.250   1.0954   0.01411   0.00821  -0.0792   0.1477   0.8858
   7.500   1.0927   0.01550   0.00936  -0.0753   0.1043   0.8883
   7.750   1.0978   0.01659   0.01032  -0.0726   0.0753   0.8909
   8.000   1.1055   0.01760   0.01124  -0.0703   0.0541   0.8935
   8.250   1.1164   0.01848   0.01209  -0.0685   0.0407   0.8961
   8.500   1.1285   0.01932   0.01290  -0.0669   0.0312   0.8987
   8.750   1.1410   0.02018   0.01374  -0.0654   0.0243   0.9015
   9.000   1.1554   0.02090   0.01449  -0.0642   0.0205   0.9046
   9.250   1.1670   0.02177   0.01537  -0.0626   0.0153   0.9088
   9.500   1.1778   0.02275   0.01635  -0.0609   0.0097   0.9134
   9.750   1.1864   0.02387   0.01750  -0.0589   0.0064   0.9194
  10.000   1.1975   0.02478   0.01851  -0.0573   0.0059   0.9284
  10.250   1.2101   0.02561   0.01949  -0.0559   0.0053   0.9560
  10.500   1.2259   0.02659   0.02054  -0.0554   0.0048   1.0000
  10.750   1.2388   0.02765   0.02164  -0.0544   0.0046   1.0000
  11.000   1.2491   0.02892   0.02298  -0.0531   0.0042   1.0000
  11.250   1.2564   0.03044   0.02458  -0.0515   0.0040   1.0000
  11.500   1.2641   0.03196   0.02619  -0.0500   0.0039   1.0000
  11.750   1.2674   0.03389   0.02825  -0.0482   0.0038   1.0000
  12.000   1.2721   0.03577   0.03023  -0.0466   0.0037   1.0000
  12.250   1.2813   0.03730   0.03185  -0.0455   0.0037   1.0000
  12.500   1.2924   0.03866   0.03329  -0.0446   0.0036   1.0000
  12.750   1.3010   0.04031   0.03504  -0.0436   0.0035   1.0000
  13.000   1.3096   0.04199   0.03682  -0.0426   0.0035   1.0000
  13.250   1.3174   0.04378   0.03870  -0.0417   0.0034   1.0000
  13.500   1.3240   0.04575   0.04079  -0.0407   0.0033   1.0000
  13.750   1.3312   0.04770   0.04284  -0.0398   0.0032   1.0000
  14.000   1.3358   0.04997   0.04524  -0.0389   0.0031   1.0000
  14.250   1.3414   0.05219   0.04757  -0.0382   0.0030   1.0000
  14.500   1.3453   0.05466   0.05016  -0.0375   0.0029   1.0000
  14.750   1.3471   0.05743   0.05308  -0.0368   0.0028   1.0000
  15.000   1.3471   0.06053   0.05634  -0.0362   0.0028   1.0000
  15.250   1.3468   0.06370   0.05966  -0.0358   0.0027   1.0000
  15.500   1.3434   0.06742   0.06355  -0.0355   0.0027   1.0000
  15.750   1.3389   0.07136   0.06765  -0.0355   0.0027   1.0000
  16.000   1.3324   0.07572   0.07219  -0.0357   0.0026   1.0000
  16.250   1.3233   0.08065   0.07730  -0.0363   0.0026   1.0000
  16.500   1.3100   0.08646   0.08332  -0.0374   0.0026   1.0000
  16.750   1.2964   0.09251   0.08957  -0.0389   0.0026   1.0000
  17.000   1.2801   0.09934   0.09662  -0.0411   0.0026   1.0000
  17.250   1.2597   0.10732   0.10480  -0.0442   0.0027   1.0000
  17.500   1.2367   0.11623   0.11394  -0.0482   0.0027   1.0000
  17.750   1.2126   0.12594   0.12386  -0.0533   0.0028   1.0000
  18.000   1.1886   0.13628   0.13441  -0.0592   0.0028   1.0000
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