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USA 40 AIRFOIL (usa40-il) Xfoil prediction polar at RE=100,000 Ncrit=5


Details Polar file
Airfoil: USA 40 AIRFOIL (usa40-il)
Reynolds number: 100,000
Max Cl/Cd: 53.22 at α=6.75°
Description: Mach=0 Ncrit=5
Source: Xfoil prediction
Download polar: xf-usa40-il-100000-n5.txt
Download as CSV file: xf-usa40-il-100000-n5.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 40 AIRFOIL                                  
  
 1 1 Reynolds number fixed          Mach number fixed         
  
 xtrf =   1.000 (top)        1.000 (bottom)  
 Mach =   0.000     Re =     0.100 e 6     Ncrit =   5.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -9.500  -0.3249   0.09602   0.09061  -0.0440   1.0000   0.0531
  -9.250  -0.3289   0.09250   0.08716  -0.0447   1.0000   0.0530
  -9.000  -0.3363   0.08891   0.08365  -0.0451   1.0000   0.0530
  -8.750  -0.3463   0.08559   0.08041  -0.0451   1.0000   0.0530
  -8.500  -0.3593   0.08274   0.07766  -0.0441   1.0000   0.0529
  -8.250  -0.3774   0.08041   0.07544  -0.0420   1.0000   0.0527
  -8.000  -0.3935   0.07741   0.07254  -0.0416   0.9982   0.0525
  -7.750  -0.3800   0.06806   0.06313  -0.0548   0.9870   0.0519
  -7.500  -0.3767   0.04981   0.04426  -0.0801   0.9714   0.0508
  -7.250  -0.3572   0.04219   0.03599  -0.0889   0.9608   0.0509
  -7.000  -0.3283   0.03731   0.03048  -0.0944   0.9535   0.0514
  -6.750  -0.2977   0.03370   0.02623  -0.0982   0.9457   0.0526
  -6.500  -0.2601   0.03127   0.02342  -0.1018   0.9413   0.0539
  -6.250  -0.2309   0.02988   0.02190  -0.1030   0.9321   0.0549
  -6.000  -0.1940   0.02822   0.02002  -0.1055   0.9264   0.0559
  -5.750  -0.1625   0.02677   0.01835  -0.1066   0.9166   0.0570
  -5.500  -0.1249   0.02528   0.01661  -0.1086   0.9089   0.0583
  -5.250  -0.0937   0.02408   0.01518  -0.1093   0.8973   0.0598
  -5.000  -0.0570   0.02298   0.01398  -0.1109   0.8894   0.0620
  -4.750  -0.0285   0.02226   0.01324  -0.1110   0.8766   0.0643
  -4.500   0.0033   0.02145   0.01233  -0.1116   0.8661   0.0671
  -4.250   0.0349   0.02064   0.01138  -0.1120   0.8551   0.0698
  -4.000   0.0635   0.01992   0.01072  -0.1121   0.8423   0.0726
  -3.750   0.0944   0.01929   0.01003  -0.1124   0.8307   0.0773
  -3.500   0.1239   0.01867   0.00939  -0.1126   0.8179   0.0833
  -3.250   0.1524   0.01818   0.00884  -0.1125   0.8038   0.0912
  -3.000   0.1814   0.01762   0.00831  -0.1125   0.7904   0.1013
  -2.750   0.2109   0.01713   0.00784  -0.1126   0.7770   0.1171
  -2.500   0.2394   0.01669   0.00754  -0.1127   0.7627   0.1438
  -2.250   0.2674   0.01634   0.00734  -0.1126   0.7477   0.1900
  -2.000   0.2955   0.01603   0.00711  -0.1125   0.7328   0.2391
  -1.750   0.3234   0.01571   0.00693  -0.1124   0.7181   0.2878
  -1.500   0.3511   0.01546   0.00679  -0.1121   0.7035   0.3425
  -1.250   0.3786   0.01525   0.00667  -0.1118   0.6885   0.4034
  -1.000   0.4049   0.01506   0.00666  -0.1112   0.6730   0.4721
  -0.750   0.4297   0.01492   0.00678  -0.1101   0.6579   0.5623
  -0.500   0.4540   0.01494   0.00691  -0.1087   0.6431   0.6392
  -0.250   0.4786   0.01502   0.00698  -0.1074   0.6284   0.6902
   0.000   0.5037   0.01512   0.00698  -0.1062   0.6139   0.7251
   0.250   0.5287   0.01522   0.00701  -0.1052   0.5984   0.7534
   0.500   0.5533   0.01530   0.00702  -0.1041   0.5833   0.7785
   0.750   0.5782   0.01538   0.00701  -0.1032   0.5685   0.8022
   1.000   0.6025   0.01544   0.00699  -0.1020   0.5542   0.8242
   1.500   0.6490   0.01544   0.00692  -0.0993   0.5260   0.8856
   1.750   0.6798   0.01538   0.00685  -0.0996   0.5117   1.0000
   2.000   0.7085   0.01564   0.00695  -0.0999   0.4987   1.0000
   2.500   0.7647   0.01620   0.00723  -0.1001   0.4744   1.0000
   2.750   0.7924   0.01651   0.00740  -0.1002   0.4638   1.0000
   3.000   0.8198   0.01683   0.00759  -0.1002   0.4536   1.0000
   3.250   0.8471   0.01715   0.00784  -0.1001   0.4437   1.0000
   3.500   0.8740   0.01751   0.00807  -0.1000   0.4346   1.0000
   3.750   0.9009   0.01785   0.00836  -0.0999   0.4251   1.0000
   4.000   0.9273   0.01822   0.00862  -0.0997   0.4164   1.0000
   4.250   0.9536   0.01858   0.00896  -0.0995   0.4073   1.0000
   4.500   0.9796   0.01897   0.00925  -0.0992   0.3990   1.0000
   4.750   1.0052   0.01934   0.00962  -0.0989   0.3896   1.0000
   5.000   1.0302   0.01972   0.00990  -0.0985   0.3802   1.0000
   5.250   1.0548   0.02008   0.01028  -0.0980   0.3695   1.0000
   5.500   1.0789   0.02048   0.01058  -0.0974   0.3602   1.0000
   5.750   1.1032   0.02085   0.01100  -0.0969   0.3505   1.0000
   6.000   1.1270   0.02126   0.01134  -0.0964   0.3424   1.0000
   6.250   1.1504   0.02164   0.01179  -0.0957   0.3323   1.0000
   6.500   1.1732   0.02207   0.01216  -0.0950   0.3236   1.0000
   6.750   1.1964   0.02248   0.01264  -0.0944   0.3153   1.0000
   7.000   1.2190   0.02295   0.01308  -0.0937   0.3089   1.0000
   7.250   1.2420   0.02339   0.01362  -0.0930   0.3015   1.0000
   7.500   1.2632   0.02386   0.01410  -0.0921   0.2937   1.0000
   7.750   1.2843   0.02434   0.01465  -0.0912   0.2845   1.0000
   8.000   1.3037   0.02486   0.01515  -0.0901   0.2757   1.0000
   8.250   1.3240   0.02538   0.01576  -0.0891   0.2670   1.0000
   8.500   1.3426   0.02595   0.01635  -0.0879   0.2597   1.0000
   8.750   1.3620   0.02652   0.01703  -0.0869   0.2523   1.0000
   9.000   1.3791   0.02715   0.01769  -0.0855   0.2446   1.0000
   9.250   1.3953   0.02781   0.01842  -0.0841   0.2352   1.0000
   9.500   1.4077   0.02855   0.01917  -0.0821   0.2257   1.0000
   9.750   1.4208   0.02934   0.02003  -0.0804   0.2155   1.0000
  10.000   1.4327   0.03023   0.02097  -0.0786   0.2055   1.0000
  10.250   1.4426   0.03125   0.02201  -0.0767   0.1961   1.0000
  10.500   1.4537   0.03228   0.02312  -0.0750   0.1873   1.0000
  10.750   1.4627   0.03347   0.02438  -0.0733   0.1793   1.0000
  11.000   1.4691   0.03488   0.02583  -0.0716   0.1688   1.0000
  11.250   1.4745   0.03646   0.02746  -0.0700   0.1576   1.0000
  11.500   1.4778   0.03827   0.02931  -0.0684   0.1466   1.0000
  11.750   1.4785   0.04043   0.03150  -0.0670   0.1348   1.0000
  12.000   1.4760   0.04299   0.03409  -0.0658   0.1229   1.0000
  12.250   1.4708   0.04599   0.03713  -0.0649   0.1124   1.0000
  12.500   1.4634   0.04943   0.04061  -0.0643   0.1044   1.0000
  12.750   1.4550   0.05319   0.04445  -0.0641   0.0987   1.0000
  13.000   1.4451   0.05733   0.04869  -0.0642   0.0945   1.0000
  13.250   1.4337   0.06187   0.05334  -0.0647   0.0907   1.0000
  13.500   1.4193   0.06698   0.05858  -0.0655   0.0876   1.0000
  13.750   1.4038   0.07249   0.06423  -0.0667   0.0852   1.0000
  14.000   1.3914   0.07776   0.06967  -0.0680   0.0830   1.0000
  14.250   1.3779   0.08332   0.07539  -0.0694   0.0808   1.0000
  14.500   1.3637   0.08914   0.08136  -0.0711   0.0786   1.0000
  14.750   1.3491   0.09511   0.08747  -0.0729   0.0767   1.0000
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