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

USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=500,000 Ncrit=5


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 500,000
Max Cl/Cd: 88.36 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40b-il-500000-n5.txt
Download as CSV file: xf-usa40b-il-500000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 B AIRFOIL                                
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.500 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
 -12.250  -0.7355   0.04509   0.04162  -0.0765   1.0000   0.0256
 -12.000  -0.7740   0.03916   0.03551  -0.0799   1.0000   0.0255
 -11.750  -0.7993   0.03564   0.03182  -0.0800   1.0000   0.0256
 -11.500  -0.7902   0.03258   0.02850  -0.0826   0.9979   0.0257
 -11.250  -0.7666   0.02989   0.02554  -0.0863   0.9942   0.0259
 -11.000  -0.7427   0.02791   0.02334  -0.0885   0.9907   0.0260
 -10.750  -0.7168   0.02624   0.02146  -0.0903   0.9869   0.0262
 -10.500  -0.6880   0.02483   0.01986  -0.0921   0.9839   0.0263
 -10.250  -0.6608   0.02332   0.01823  -0.0935   0.9806   0.0265
 -10.000  -0.6350   0.02211   0.01692  -0.0941   0.9758   0.0267
  -9.500  -0.5734   0.02020   0.01487  -0.0967   0.9697   0.0271
  -9.250  -0.5482   0.01943   0.01405  -0.0967   0.9630   0.0273
  -9.000  -0.5173   0.01865   0.01319  -0.0977   0.9589   0.0275
  -8.750  -0.4863   0.01793   0.01241  -0.0986   0.9542   0.0278
  -8.500  -0.4561   0.01726   0.01168  -0.0993   0.9476   0.0281
  -8.250  -0.4181   0.01657   0.01091  -0.1014   0.9419   0.0285
  -8.000  -0.3807   0.01590   0.01016  -0.1034   0.9288   0.0289
  -7.750  -0.3384   0.01523   0.00935  -0.1064   0.9097   0.0293
  -7.500  -0.3044   0.01469   0.00867  -0.1075   0.8846   0.0296
  -7.250  -0.2757   0.01427   0.00811  -0.1076   0.8576   0.0299
  -7.000  -0.2490   0.01392   0.00761  -0.1071   0.8294   0.0301
  -6.750  -0.2241   0.01357   0.00710  -0.1064   0.7958   0.0304
  -6.500  -0.1999   0.01323   0.00661  -0.1055   0.7659   0.0307
  -6.000  -0.1498   0.01273   0.00589  -0.1041   0.7258   0.0315
  -5.750  -0.1239   0.01250   0.00557  -0.1035   0.7103   0.0319
  -5.500  -0.0978   0.01228   0.00527  -0.1030   0.6957   0.0323
  -5.250  -0.0715   0.01208   0.00499  -0.1025   0.6818   0.0329
  -5.000  -0.0452   0.01189   0.00472  -0.1019   0.6669   0.0334
  -4.750  -0.0185   0.01171   0.00445  -0.1015   0.6516   0.0340
  -4.500   0.0079   0.01154   0.00421  -0.1009   0.6344   0.0347
  -4.250   0.0343   0.01136   0.00397  -0.1004   0.6161   0.0357
  -4.000   0.0606   0.01123   0.00376  -0.0999   0.5961   0.0366
  -3.750   0.0867   0.01115   0.00357  -0.0993   0.5717   0.0377
  -3.500   0.1124   0.01112   0.00339  -0.0986   0.5405   0.0388
  -3.250   0.1378   0.01111   0.00324  -0.0979   0.5061   0.0403
  -3.000   0.1634   0.01113   0.00312  -0.0972   0.4737   0.0423
  -2.750   0.1893   0.01115   0.00302  -0.0966   0.4465   0.0451
  -2.500   0.2155   0.01116   0.00295  -0.0961   0.4238   0.0495
  -2.250   0.2419   0.01117   0.00289  -0.0956   0.4038   0.0565
  -2.000   0.2684   0.01118   0.00285  -0.0951   0.3858   0.0652
  -1.500   0.3222   0.01118   0.00276  -0.0943   0.3580   0.0819
  -1.250   0.3491   0.01117   0.00272  -0.0939   0.3477   0.0918
  -1.000   0.3760   0.01111   0.00269  -0.0936   0.3380   0.1108
  -0.750   0.4025   0.01100   0.00270  -0.0932   0.3294   0.1579
  -0.500   0.4295   0.01098   0.00272  -0.0929   0.3207   0.1900
  -0.250   0.4563   0.01099   0.00275  -0.0925   0.3129   0.2144
   0.000   0.4833   0.01094   0.00277  -0.0921   0.3060   0.2441
   0.250   0.5099   0.01087   0.00281  -0.0918   0.2994   0.2908
   0.500   0.5364   0.01076   0.00288  -0.0914   0.2941   0.3645
   0.750   0.5631   0.01070   0.00294  -0.0911   0.2886   0.4161
   1.000   0.5894   0.01065   0.00301  -0.0906   0.2828   0.4729
   1.250   0.6154   0.01061   0.00312  -0.0901   0.2778   0.5406
   1.500   0.6417   0.01060   0.00324  -0.0895   0.2727   0.5963
   1.750   0.6679   0.01066   0.00336  -0.0890   0.2673   0.6373
   2.000   0.6937   0.01076   0.00350  -0.0883   0.2625   0.6714
   2.250   0.7202   0.01084   0.00362  -0.0878   0.2590   0.6982
   2.500   0.7466   0.01094   0.00374  -0.0872   0.2550   0.7182
   2.750   0.7729   0.01107   0.00386  -0.0867   0.2510   0.7354
   3.000   0.7987   0.01121   0.00399  -0.0861   0.2472   0.7488
   3.250   0.8247   0.01134   0.00413  -0.0855   0.2439   0.7616
   3.500   0.8511   0.01146   0.00426  -0.0850   0.2410   0.7740
   3.750   0.8770   0.01158   0.00439  -0.0844   0.2376   0.7858
   4.000   0.9024   0.01171   0.00453  -0.0837   0.2341   0.7997
   4.250   0.9274   0.01187   0.00469  -0.0830   0.2308   0.8140
   4.500   0.9523   0.01200   0.00485  -0.0823   0.2280   0.8295
   4.750   0.9770   0.01206   0.00499  -0.0814   0.2260   0.8544
   5.000   1.0161   0.01204   0.00515  -0.0837   0.2232   1.0000
   5.250   1.0421   0.01224   0.00533  -0.0832   0.2208   1.0000
   5.500   1.0677   0.01246   0.00552  -0.0827   0.2184   1.0000
   5.750   1.0929   0.01269   0.00573  -0.0822   0.2161   1.0000
   6.000   1.1177   0.01295   0.00595  -0.0816   0.2137   1.0000
   6.250   1.1430   0.01317   0.00617  -0.0810   0.2119   1.0000
   6.500   1.1684   0.01337   0.00638  -0.0805   0.2099   1.0000
   6.750   1.1935   0.01358   0.00659  -0.0799   0.2076   1.0000
   7.000   1.2182   0.01381   0.00683  -0.0793   0.2055   1.0000
   7.250   1.2424   0.01406   0.00708  -0.0786   0.2034   1.0000
   7.500   1.2661   0.01433   0.00733  -0.0779   0.2011   1.0000
   7.750   1.2891   0.01464   0.00762  -0.0770   0.1988   1.0000
   8.000   1.3126   0.01491   0.00791  -0.0762   0.1971   1.0000
   8.250   1.3364   0.01515   0.00818  -0.0755   0.1958   1.0000
   8.500   1.3598   0.01540   0.00846  -0.0747   0.1944   1.0000
   8.750   1.3828   0.01566   0.00875  -0.0739   0.1926   1.0000
   9.000   1.4052   0.01594   0.00906  -0.0730   0.1907   1.0000
   9.250   1.4271   0.01624   0.00937  -0.0720   0.1891   1.0000
   9.500   1.4482   0.01655   0.00970  -0.0708   0.1876   1.0000
   9.750   1.4677   0.01688   0.01005  -0.0695   0.1861   1.0000
  10.000   1.4860   0.01725   0.01043  -0.0679   0.1845   1.0000
  10.250   1.5041   0.01762   0.01083  -0.0663   0.1830   1.0000
  10.500   1.5238   0.01793   0.01119  -0.0650   0.1818   1.0000
  10.750   1.5431   0.01824   0.01157  -0.0636   0.1805   1.0000
  11.000   1.5618   0.01860   0.01198  -0.0622   0.1790   1.0000
  11.250   1.5799   0.01897   0.01240  -0.0608   0.1774   1.0000
  11.500   1.5973   0.01937   0.01284  -0.0593   0.1755   1.0000
  11.750   1.6139   0.01981   0.01332  -0.0578   0.1736   1.0000
  12.000   1.6295   0.02031   0.01384  -0.0561   0.1718   1.0000
  12.250   1.6433   0.02090   0.01445  -0.0544   0.1696   1.0000
  12.500   1.6608   0.02133   0.01497  -0.0531   0.1678   1.0000
  12.750   1.6773   0.02181   0.01553  -0.0517   0.1653   1.0000
  13.000   1.6923   0.02238   0.01614  -0.0503   0.1623   1.0000
  13.250   1.7054   0.02306   0.01686  -0.0487   0.1592   1.0000
  13.500   1.7164   0.02388   0.01770  -0.0471   0.1560   1.0000
  13.750   1.7314   0.02452   0.01842  -0.0459   0.1525   1.0000
  14.000   1.7432   0.02537   0.01931  -0.0445   0.1479   1.0000
  14.250   1.7514   0.02648   0.02044  -0.0429   0.1440   1.0000
  14.500   1.7632   0.02742   0.02145  -0.0417   0.1398   1.0000
  14.750   1.7706   0.02869   0.02275  -0.0403   0.1340   1.0000
  15.000   1.7768   0.03013   0.02422  -0.0391   0.1279   1.0000
  15.250   1.7790   0.03197   0.02608  -0.0378   0.1205   1.0000
  15.500   1.7758   0.03440   0.02850  -0.0367   0.1100   1.0000
  15.750   1.7672   0.03749   0.03159  -0.0358   0.1001   1.0000
  16.000   1.7583   0.04080   0.03493  -0.0352   0.0940   1.0000
  16.250   1.7477   0.04446   0.03866  -0.0350   0.0897   1.0000
  16.500   1.7393   0.04808   0.04236  -0.0351   0.0868   1.0000
  16.750   1.7260   0.05247   0.04685  -0.0357   0.0842   1.0000
  17.000   1.7102   0.05742   0.05191  -0.0366   0.0822   1.0000
  17.250   1.6979   0.06214   0.05676  -0.0378   0.0807   1.0000
  17.500   1.6827   0.06749   0.06224  -0.0394   0.0792   1.0000
  17.750   1.6631   0.07366   0.06854  -0.0414   0.0779   1.0000
  18.000   1.6400   0.08056   0.07559  -0.0440   0.0767   1.0000
  18.250   1.6140   0.08807   0.08324  -0.0470   0.0757   1.0000
  18.500   1.5869   0.09592   0.09122  -0.0502   0.0747   1.0000
<< Back to USA 40 B AIRFOIL (usa40b-il)

Polar data table (+)

Polar graphs


<< Back to USA 40 B AIRFOIL (usa40b-il)