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74-130 WP2 MOD (fx74130wp2mod-il) Xfoil prediction polar at RE=200,000 Ncrit=9


Details Polar file
Airfoil: 74-130 WP2 MOD (fx74130wp2mod-il)
Reynolds number: 200,000
Max Cl/Cd: 82.13 at α=7.5°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-fx74130wp2mod-il-200000.txt
Download as CSV file: xf-fx74130wp2mod-il-200000.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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -10.000  -0.1456   0.09154   0.08792  -0.1080   0.9355   0.0380
  -9.750  -0.1420   0.08795   0.08434  -0.1138   0.9314   0.0387
  -9.500  -0.1396   0.08451   0.08091  -0.1176   0.9275   0.0389
  -9.250  -0.1407   0.08062   0.07703  -0.1219   0.9226   0.0390
  -9.000  -0.1453   0.07675   0.07311  -0.1260   0.9181   0.0391
  -8.750  -0.1545   0.07399   0.07031  -0.1271   0.9135   0.0391
  -8.500  -0.1638   0.07181   0.06806  -0.1268   0.9088   0.0392
  -8.250  -0.1532   0.06526   0.06165  -0.1266   0.9073   0.0410
  -8.000  -0.1515   0.06296   0.05932  -0.1260   0.9038   0.0420
  -7.750  -0.1527   0.06057   0.05690  -0.1257   0.8994   0.0428
  -7.500  -0.1539   0.05814   0.05441  -0.1253   0.8943   0.0437
  -7.250  -0.1525   0.05552   0.05167  -0.1250   0.8901   0.0452
  -7.000  -0.1510   0.05301   0.04904  -0.1244   0.8860   0.0471
  -6.750  -0.1485   0.05101   0.04676  -0.1234   0.8811   0.0505
  -6.500  -0.1466   0.05061   0.04577  -0.1211   0.8767   0.0523
  -6.250  -0.1370   0.04481   0.04011  -0.1214   0.8744   0.0544
  -6.000  -0.1279   0.04308   0.03839  -0.1200   0.8698   0.0563
  -5.750  -0.1152   0.04125   0.03640  -0.1188   0.8658   0.0605
  -5.500  -0.1022   0.03906   0.03372  -0.1175   0.8625   0.0676
  -5.250  -0.0847   0.03694   0.03162  -0.1169   0.8596   0.0710
  -5.000  -0.0754   0.03596   0.03025  -0.1146   0.8538   0.0813
  -4.750  -0.0552   0.03383   0.02813  -0.1142   0.8506   0.0862
  -4.500  -0.0332   0.03209   0.02617  -0.1139   0.8481   0.0995
  -4.250  -0.0015   0.02719   0.02012  -0.1096   0.8443   0.0369
  -4.000   0.0180   0.02532   0.01800  -0.1080   0.8393   0.0340
  -3.750   0.0453   0.02419   0.01661  -0.1075   0.8363   0.0361
  -3.500   0.0749   0.02281   0.01502  -0.1073   0.8343   0.0363
  -3.250   0.0930   0.02208   0.01422  -0.1055   0.8289   0.0359
  -3.000   0.1154   0.02126   0.01332  -0.1044   0.8245   0.0361
  -2.750   0.1423   0.02041   0.01241  -0.1039   0.8218   0.0375
  -2.500   0.1700   0.01951   0.01145  -0.1037   0.8197   0.0406
  -2.250   0.1831   0.01936   0.01130  -0.1015   0.8118   0.0497
  -2.000   0.1876   0.01641   0.01106  -0.0976   0.8083   0.6829
  -1.750   0.1980   0.01716   0.01192  -0.0912   0.8060   0.8376
  -1.500   0.1925   0.01790   0.01272  -0.0836   0.7969   0.8708
  -1.250   0.2004   0.01805   0.01279  -0.0774   0.7939   0.9022
  -1.000   0.3002   0.01835   0.01288  -0.0879   0.7955   0.9541
  -0.750   0.3591   0.01812   0.01246  -0.0941   0.7942   0.9611
  -0.500   0.4062   0.01789   0.01208  -0.0981   0.7927   0.9661
  -0.250   0.4294   0.01815   0.01231  -0.0981   0.7855   0.9723
   0.000   0.4696   0.01800   0.01207  -0.1011   0.7824   0.9756
   0.250   0.5062   0.01782   0.01181  -0.1031   0.7801   0.9789
   0.500   0.5393   0.01766   0.01158  -0.1044   0.7782   0.9819
   0.750   0.5622   0.01804   0.01198  -0.1047   0.7701   0.9859
   1.000   0.5974   0.01787   0.01176  -0.1065   0.7673   0.9883
   1.250   0.6318   0.01766   0.01151  -0.1080   0.7652   0.9905
   1.500   0.6524   0.01807   0.01196  -0.1077   0.7578   0.9940
   1.750   0.6843   0.01800   0.01189  -0.1090   0.7545   0.9960
   2.000   0.7176   0.01784   0.01172  -0.1104   0.7523   0.9978
   2.250   0.7499   0.01775   0.01163  -0.1116   0.7500   0.9996
   2.500   0.7563   0.01837   0.01231  -0.1086   0.7414   1.0000
   2.750   0.7806   0.01824   0.01222  -0.1081   0.7389   1.0000
   3.000   0.8065   0.01810   0.01209  -0.1078   0.7370   1.0000
   3.250   0.8026   0.01899   0.01306  -0.1030   0.7278   1.0000
   3.500   0.8266   0.01887   0.01297  -0.1025   0.7253   1.0000
   3.750   0.8531   0.01870   0.01283  -0.1023   0.7236   1.0000
   4.000   0.8405   0.01973   0.01394  -0.0960   0.7140   1.0000
   4.250   0.8657   0.01953   0.01382  -0.0955   0.7118   1.0000
   4.500   0.8836   0.01946   0.01381  -0.0938   0.7078   1.0000
   4.750   0.8838   0.01972   0.01412  -0.0891   0.7001   1.0000
   5.000   0.9165   0.01917   0.01364  -0.0897   0.6980   1.0000
   5.250   0.9120   0.01961   0.01415  -0.0844   0.6897   1.0000
   5.500   0.9542   0.01846   0.01310  -0.0861   0.6861   1.0000
   5.750   0.9944   0.01724   0.01195  -0.0874   0.6805   1.0000
   6.000   1.0245   0.01633   0.01112  -0.0872   0.6718   1.0000
   6.250   1.0504   0.01560   0.01047  -0.0863   0.6606   1.0000
   6.500   1.0791   0.01486   0.00983  -0.0859   0.6471   1.0000
   6.750   1.1093   0.01419   0.00916  -0.0858   0.6294   1.0000
   7.000   1.1298   0.01412   0.00916  -0.0844   0.6095   1.0000
   7.250   1.1542   0.01406   0.00910  -0.0837   0.5873   1.0000
   7.500   1.1712   0.01426   0.00930  -0.0819   0.5588   1.0000
   7.750   1.1804   0.01467   0.00969  -0.0788   0.5183   1.0000
   8.000   1.1764   0.01541   0.01021  -0.0736   0.4501   1.0000
   8.250   1.1556   0.01716   0.01138  -0.0666   0.3625   1.0000
   8.500   1.1360   0.01949   0.01322  -0.0610   0.2883   1.0000
   8.750   1.1184   0.02210   0.01535  -0.0563   0.2136   1.0000
   9.000   1.1027   0.02488   0.01760  -0.0522   0.1389   1.0000
   9.250   1.0921   0.02754   0.01985  -0.0488   0.0895   1.0000
   9.500   1.0890   0.02980   0.02192  -0.0461   0.0676   1.0000
   9.750   1.0888   0.03192   0.02400  -0.0439   0.0551   1.0000
  10.000   1.0943   0.03367   0.02578  -0.0422   0.0456   1.0000
  10.250   1.0987   0.03556   0.02772  -0.0405   0.0377   1.0000
  10.500   1.0980   0.03799   0.03013  -0.0383   0.0327   1.0000
  10.750   1.1079   0.03966   0.03193  -0.0369   0.0283   1.0000
  11.000   1.1165   0.04142   0.03368  -0.0357   0.0246   1.0000
  11.250   1.1304   0.04334   0.03571  -0.0342   0.0218   1.0000
  11.500   1.1509   0.04486   0.03737  -0.0332   0.0200   1.0000
  11.750   1.1749   0.04653   0.03921  -0.0325   0.0187   1.0000
  12.000   1.1995   0.04857   0.04145  -0.0319   0.0180   1.0000
  12.250   1.2224   0.05122   0.04439  -0.0313   0.0177   1.0000
  12.500   1.2390   0.05474   0.04829  -0.0302   0.0178   1.0000
  12.750   1.2424   0.05914   0.05316  -0.0286   0.0184   1.0000
  13.000   1.2360   0.06392   0.05835  -0.0267   0.0190   1.0000
  13.250   1.2249   0.06880   0.06358  -0.0251   0.0197   1.0000
  13.500   1.2097   0.07383   0.06891  -0.0239   0.0203   1.0000
  13.750   1.1923   0.07899   0.07434  -0.0231   0.0208   1.0000
  14.000   1.1739   0.08428   0.07987  -0.0230   0.0212   1.0000
  14.250   1.1541   0.08993   0.08573  -0.0234   0.0215   1.0000
  14.500   1.1333   0.09610   0.09210  -0.0245   0.0219   1.0000
  14.750   0.9592   0.09592   0.09256  -0.0205   0.0207   1.0000
  15.000   0.9355   0.10183   0.09865  -0.0234   0.0210   1.0000
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