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USA 40 B AIRFOIL (usa40b-il) Xfoil prediction polar at RE=200,000 Ncrit=5


Details Polar file
Airfoil: USA 40 B AIRFOIL (usa40b-il)
Reynolds number: 200,000
Max Cl/Cd: 62 at α=7.25°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40b-il-200000-n5.txt
Download as CSV file: xf-usa40b-il-200000-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 =     0.200 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.750  -0.3209   0.09380   0.08991  -0.0360   1.0000   0.0377
  -9.500  -0.3253   0.08988   0.08603  -0.0370   1.0000   0.0374
  -9.000  -0.5480   0.04044   0.03576  -0.0739   0.9906   0.0351
  -8.750  -0.5246   0.03648   0.03145  -0.0788   0.9839   0.0353
  -8.500  -0.4984   0.03403   0.02876  -0.0816   0.9775   0.0358
  -8.250  -0.4693   0.03172   0.02621  -0.0844   0.9718   0.0363
  -8.000  -0.4425   0.02946   0.02365  -0.0864   0.9646   0.0369
  -7.750  -0.4121   0.02722   0.02107  -0.0886   0.9586   0.0375
  -7.500  -0.3835   0.02534   0.01888  -0.0899   0.9513   0.0379
  -7.250  -0.3516   0.02367   0.01692  -0.0915   0.9448   0.0384
  -7.000  -0.3187   0.02225   0.01523  -0.0929   0.9358   0.0388
  -6.750  -0.2773   0.02093   0.01375  -0.0957   0.9255   0.0393
  -6.500  -0.2399   0.01994   0.01270  -0.0976   0.9095   0.0399
  -6.250  -0.2051   0.01912   0.01180  -0.0989   0.8943   0.0405
  -6.000  -0.1715   0.01840   0.01100  -0.1000   0.8799   0.0413
  -5.750  -0.1383   0.01772   0.01022  -0.1009   0.8640   0.0424
  -5.500  -0.1063   0.01709   0.00945  -0.1015   0.8450   0.0435
  -5.250  -0.0757   0.01649   0.00874  -0.1018   0.8235   0.0445
  -5.000  -0.0460   0.01599   0.00818  -0.1020   0.8007   0.0454
  -4.750  -0.0174   0.01558   0.00766  -0.1018   0.7781   0.0464
  -4.500   0.0099   0.01523   0.00718  -0.1014   0.7573   0.0477
  -4.250   0.0367   0.01492   0.00672  -0.1009   0.7377   0.0491
  -4.000   0.0630   0.01463   0.00634  -0.1004   0.7193   0.0506
  -3.750   0.0894   0.01443   0.00605  -0.0998   0.7020   0.0529
  -3.500   0.1156   0.01424   0.00574  -0.0992   0.6845   0.0559
  -3.250   0.1416   0.01404   0.00549  -0.0986   0.6662   0.0593
  -3.000   0.1676   0.01385   0.00522  -0.0980   0.6469   0.0638
  -2.750   0.1935   0.01367   0.00497  -0.0973   0.6255   0.0696
  -2.500   0.2192   0.01350   0.00473  -0.0967   0.6019   0.0771
  -2.250   0.2444   0.01336   0.00451  -0.0959   0.5753   0.0874
  -2.000   0.2693   0.01325   0.00431  -0.0951   0.5453   0.1013
  -1.750   0.2935   0.01316   0.00417  -0.0943   0.5132   0.1245
  -1.500   0.3176   0.01310   0.00413  -0.0935   0.4825   0.1698
  -1.250   0.3423   0.01311   0.00410  -0.0928   0.4563   0.2090
  -1.000   0.3672   0.01308   0.00408  -0.0921   0.4345   0.2480
  -0.750   0.3919   0.01303   0.00410  -0.0915   0.4156   0.2958
  -0.500   0.4169   0.01301   0.00414  -0.0909   0.3991   0.3501
  -0.250   0.4419   0.01299   0.00420  -0.0902   0.3849   0.4083
   0.000   0.4663   0.01293   0.00430  -0.0894   0.3722   0.4792
   0.250   0.4906   0.01289   0.00446  -0.0884   0.3618   0.5604
   0.500   0.5144   0.01297   0.00464  -0.0873   0.3524   0.6244
   0.750   0.5392   0.01306   0.00479  -0.0863   0.3438   0.6700
   1.000   0.5637   0.01322   0.00492  -0.0853   0.3354   0.7044
   1.250   0.5889   0.01337   0.00505  -0.0845   0.3278   0.7333
   1.500   0.6141   0.01353   0.00516  -0.0837   0.3203   0.7543
   1.750   0.6390   0.01372   0.00528  -0.0828   0.3140   0.7713
   2.000   0.6644   0.01383   0.00540  -0.0821   0.3082   0.7883
   2.250   0.6890   0.01396   0.00551  -0.0811   0.3025   0.8077
   2.500   0.7132   0.01412   0.00563  -0.0802   0.2975   0.8288
   2.750   0.7393   0.01420   0.00575  -0.0796   0.2926   0.8529
   3.000   0.7677   0.01427   0.00586  -0.0794   0.2871   0.8859
   3.250   0.8048   0.01444   0.00601  -0.0813   0.2817   1.0000
   3.500   0.8310   0.01471   0.00620  -0.0810   0.2775   1.0000
   3.750   0.8578   0.01495   0.00640  -0.0807   0.2732   1.0000
   4.000   0.8840   0.01521   0.00661  -0.0803   0.2693   1.0000
   4.250   0.9097   0.01550   0.00683  -0.0799   0.2657   1.0000
   4.500   0.9349   0.01584   0.00708  -0.0794   0.2625   1.0000
   4.750   0.9608   0.01612   0.00735  -0.0790   0.2594   1.0000
   5.000   0.9867   0.01640   0.00762  -0.0786   0.2562   1.0000
   5.250   1.0121   0.01669   0.00790  -0.0781   0.2530   1.0000
   5.500   1.0371   0.01701   0.00817  -0.0775   0.2499   1.0000
   5.750   1.0616   0.01736   0.00847  -0.0769   0.2470   1.0000
   6.000   1.0861   0.01775   0.00880  -0.0764   0.2444   1.0000
   6.250   1.1112   0.01806   0.00915  -0.0758   0.2420   1.0000
   6.500   1.1360   0.01839   0.00951  -0.0753   0.2395   1.0000
   6.750   1.1604   0.01874   0.00988  -0.0747   0.2372   1.0000
   7.000   1.1845   0.01911   0.01024  -0.0741   0.2349   1.0000
   7.250   1.2083   0.01949   0.01062  -0.0734   0.2329   1.0000
   7.500   1.2319   0.01991   0.01102  -0.0727   0.2309   1.0000
   7.750   1.2554   0.02040   0.01146  -0.0721   0.2291   1.0000
   8.000   1.2790   0.02081   0.01193  -0.0714   0.2273   1.0000
   8.250   1.3021   0.02121   0.01240  -0.0707   0.2253   1.0000
   8.500   1.3246   0.02160   0.01286  -0.0699   0.2228   1.0000
   8.750   1.3465   0.02200   0.01330  -0.0690   0.2204   1.0000
   9.000   1.3681   0.02242   0.01376  -0.0681   0.2182   1.0000
   9.250   1.3894   0.02287   0.01422  -0.0672   0.2163   1.0000
   9.500   1.4109   0.02337   0.01472  -0.0663   0.2146   1.0000
   9.750   1.4323   0.02393   0.01526  -0.0654   0.2127   1.0000
  10.000   1.4516   0.02438   0.01585  -0.0642   0.2108   1.0000
  10.250   1.4705   0.02487   0.01644  -0.0630   0.2087   1.0000
  10.500   1.4885   0.02537   0.01703  -0.0616   0.2068   1.0000
  10.750   1.5062   0.02590   0.01764  -0.0602   0.2052   1.0000
  11.000   1.5232   0.02645   0.01826  -0.0587   0.2036   1.0000
  11.250   1.5395   0.02700   0.01887  -0.0571   0.2019   1.0000
  11.500   1.5554   0.02757   0.01947  -0.0556   0.2003   1.0000
  11.750   1.5720   0.02820   0.02011  -0.0542   0.1985   1.0000
  12.000   1.5862   0.02889   0.02089  -0.0526   0.1967   1.0000
  12.250   1.5979   0.02960   0.02176  -0.0507   0.1948   1.0000
  12.500   1.6097   0.03036   0.02266  -0.0489   0.1929   1.0000
  12.750   1.6206   0.03114   0.02356  -0.0472   0.1908   1.0000
  13.000   1.6313   0.03196   0.02447  -0.0455   0.1888   1.0000
  13.250   1.6420   0.03283   0.02543  -0.0439   0.1871   1.0000
  13.500   1.6529   0.03374   0.02640  -0.0424   0.1854   1.0000
  13.750   1.6647   0.03468   0.02737  -0.0411   0.1838   1.0000
  14.000   1.6720   0.03589   0.02872  -0.0397   0.1821   1.0000
  14.250   1.6764   0.03730   0.03032  -0.0381   0.1800   1.0000
  14.500   1.6800   0.03881   0.03199  -0.0368   0.1776   1.0000
  14.750   1.6829   0.04038   0.03370  -0.0356   0.1749   1.0000
  15.000   1.6862   0.04198   0.03537  -0.0346   0.1722   1.0000
  15.250   1.6902   0.04358   0.03696  -0.0338   0.1693   1.0000
  15.500   1.6851   0.04625   0.03988  -0.0333   0.1659   1.0000
  15.750   1.6810   0.04896   0.04276  -0.0331   0.1621   1.0000
  16.000   1.6779   0.05166   0.04553  -0.0330   0.1586   1.0000
  16.250   1.6733   0.05468   0.04864  -0.0332   0.1554   1.0000
  16.500   1.6633   0.05867   0.05285  -0.0340   0.1517   1.0000
  16.750   1.6524   0.06294   0.05727  -0.0350   0.1481   1.0000
  17.000   1.6407   0.06746   0.06186  -0.0364   0.1446   1.0000
  17.250   1.6208   0.07353   0.06814  -0.0386   0.1410   1.0000
  17.500   1.5931   0.08112   0.07593  -0.0418   0.1371   1.0000
  17.750   1.5648   0.08910   0.08402  -0.0454   0.1332   1.0000
  18.000   1.5150   0.10110   0.09625  -0.0512   0.1297   1.0000
  18.250   1.4203   0.12182   0.11725  -0.0621   0.1248   1.0000
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