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USA 26 AIRFOIL (usa26-il) Xfoil prediction polar at RE=500,000 Ncrit=9


Details Polar file
Airfoil: USA 26 AIRFOIL (usa26-il)
Reynolds number: 500,000
Max Cl/Cd: 95.91 at α=7°
Description: Mach=0 Ncrit=9
Source: Xfoil prediction
Download polar: xf-usa26-il-500000.txt
Download as CSV file: xf-usa26-il-500000.csv

  
       XFOIL         Version 6.96
  
 Calculated polar for: USA 26 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 =   9.000
  
   alpha    CL        CD       CDp       CM     Top_Xtr  Bot_Xtr
  ------ -------- --------- --------- -------- -------- --------
  -8.750  -0.3702   0.09610   0.09396  -0.0243   1.0000   0.0250
  -8.500  -0.3739   0.09395   0.09184  -0.0233   1.0000   0.0254
  -8.250  -0.3791   0.09198   0.08991  -0.0221   1.0000   0.0260
  -8.000  -0.3716   0.08828   0.08621  -0.0258   0.9982   0.0275
  -7.750  -0.3618   0.08077   0.07868  -0.0413   0.9907   0.0292
  -7.500  -0.3384   0.07398   0.07183  -0.0512   0.9858   0.0294
  -7.250  -0.3263   0.06606   0.06386  -0.0580   0.9823   0.0300
  -7.000  -0.3065   0.06357   0.06135  -0.0596   0.9770   0.0305
  -6.750  -0.2781   0.06074   0.05848  -0.0635   0.9737   0.0314
  -6.500  -0.2488   0.05689   0.05455  -0.0689   0.9713   0.0333
  -6.250  -0.2213   0.04792   0.04520  -0.0771   0.9627   0.0367
  -6.000  -0.2098   0.03921   0.03622  -0.0807   0.9586   0.0378
  -5.750  -0.1787   0.03759   0.03460  -0.0830   0.9572   0.0386
  -5.500  -0.1600   0.03623   0.03320  -0.0824   0.9500   0.0396
  -5.250  -0.1317   0.03347   0.03027  -0.0842   0.9465   0.0418
  -5.000  -0.0951   0.03185   0.02803  -0.0857   0.9440   0.0460
  -4.750  -0.0880   0.02548   0.02129  -0.0843   0.9369   0.0477
  -4.500  -0.0606   0.02380   0.01961  -0.0849   0.9323   0.0489
  -4.250  -0.0287   0.02237   0.01808  -0.0862   0.9289   0.0511
  -4.000  -0.0066   0.02127   0.01678  -0.0849   0.9205   0.0542
  -3.750   0.0296   0.02267   0.01789  -0.0854   0.9146   0.0576
  -3.500   0.0435   0.01634   0.01097  -0.0825   0.9051   0.0437
  -3.250   0.0760   0.01502   0.00943  -0.0833   0.8984   0.0437
  -3.000   0.1018   0.01387   0.00810  -0.0825   0.8867   0.0432
  -2.750   0.1314   0.01293   0.00700  -0.0826   0.8748   0.0432
  -2.500   0.1620   0.01217   0.00611  -0.0829   0.8604   0.0434
  -2.250   0.1923   0.01155   0.00537  -0.0831   0.8426   0.0437
  -2.000   0.2210   0.01106   0.00474  -0.0830   0.8212   0.0442
  -1.750   0.2474   0.01080   0.00435  -0.0824   0.7967   0.0451
  -1.500   0.2721   0.01067   0.00408  -0.0814   0.7687   0.0459
  -1.250   0.2939   0.01027   0.00352  -0.0799   0.7352   0.0466
  -1.000   0.3130   0.00994   0.00302  -0.0778   0.6937   0.0481
  -0.750   0.3307   0.00993   0.00279  -0.0755   0.6430   0.0495
  -0.500   0.3486   0.01000   0.00264  -0.0733   0.5964   0.0513
  -0.250   0.3686   0.01007   0.00254  -0.0715   0.5641   0.0534
   0.000   0.3903   0.01011   0.00245  -0.0701   0.5410   0.0558
   0.250   0.4125   0.01010   0.00234  -0.0688   0.5230   0.0605
   0.500   0.4351   0.01007   0.00224  -0.0676   0.5077   0.0683
   0.750   0.4545   0.00969   0.00219  -0.0659   0.4950   0.2005
   1.000   0.4764   0.00961   0.00231  -0.0648   0.4827   0.2921
   1.250   0.4993   0.00964   0.00237  -0.0637   0.4708   0.3319
   1.500   0.5221   0.00959   0.00242  -0.0627   0.4593   0.3803
   1.750   0.5249   0.00848   0.00242  -0.0575   0.4510   0.7804
   2.000   0.6792   0.00906   0.00320  -0.0849   0.4279   0.9914
   2.250   0.7462   0.00922   0.00322  -0.0936   0.4130   1.0000
   2.500   0.7681   0.00934   0.00328  -0.0924   0.4041   1.0000
   2.750   0.7892   0.00949   0.00335  -0.0911   0.3956   1.0000
   3.000   0.8115   0.00959   0.00343  -0.0899   0.3883   1.0000
   3.250   0.8330   0.00974   0.00352  -0.0886   0.3824   1.0000
   3.500   0.8548   0.00987   0.00364  -0.0874   0.3773   1.0000
   3.750   0.8768   0.00999   0.00374  -0.0861   0.3717   1.0000
   4.000   0.8978   0.01016   0.00386  -0.0848   0.3661   1.0000
   4.250   0.9197   0.01028   0.00400  -0.0836   0.3613   1.0000
   4.500   0.9415   0.01041   0.00413  -0.0823   0.3564   1.0000
   4.750   0.9624   0.01058   0.00427  -0.0809   0.3520   1.0000
   5.000   0.9837   0.01073   0.00442  -0.0796   0.3469   1.0000
   5.250   1.0049   0.01085   0.00456  -0.0783   0.3406   1.0000
   5.500   1.0247   0.01105   0.00471  -0.0767   0.3336   1.0000
   5.750   1.0459   0.01114   0.00484  -0.0753   0.3262   1.0000
   6.000   1.0654   0.01134   0.00501  -0.0737   0.3200   1.0000
   6.250   1.0867   0.01145   0.00518  -0.0724   0.3144   1.0000
   6.500   1.1064   0.01162   0.00535  -0.0708   0.3073   1.0000
   6.750   1.1265   0.01176   0.00552  -0.0693   0.2998   1.0000
   7.000   1.1452   0.01194   0.00567  -0.0675   0.2870   1.0000
   7.250   1.1640   0.01214   0.00585  -0.0658   0.2728   1.0000
   7.500   1.1823   0.01237   0.00604  -0.0640   0.2529   1.0000
   7.750   1.1958   0.01286   0.00632  -0.0614   0.2113   1.0000
   8.000   1.2022   0.01384   0.00695  -0.0577   0.1616   1.0000
   8.250   1.2118   0.01463   0.00756  -0.0545   0.1326   1.0000
   8.500   1.2217   0.01533   0.00811  -0.0513   0.1055   1.0000
   8.750   1.2154   0.01672   0.00911  -0.0454   0.0456   1.0000
   9.000   1.2165   0.01776   0.01000  -0.0407   0.0226   1.0000
   9.250   1.2282   0.01830   0.01059  -0.0379   0.0203   1.0000
   9.500   1.2396   0.01889   0.01126  -0.0352   0.0191   1.0000
   9.750   1.2489   0.01961   0.01206  -0.0322   0.0179   1.0000
  10.000   1.2559   0.02049   0.01304  -0.0290   0.0167   1.0000
  10.250   1.2637   0.02135   0.01399  -0.0260   0.0162   1.0000
  10.500   1.2720   0.02220   0.01493  -0.0233   0.0159   1.0000
  10.750   1.2790   0.02315   0.01597  -0.0205   0.0154   1.0000
  11.000   1.2834   0.02430   0.01721  -0.0176   0.0149   1.0000
  11.250   1.2869   0.02556   0.01856  -0.0148   0.0146   1.0000
  11.500   1.2895   0.02695   0.02004  -0.0122   0.0143   1.0000
  11.750   1.2894   0.02862   0.02182  -0.0096   0.0139   1.0000
  12.000   1.2883   0.03050   0.02380  -0.0073   0.0138   1.0000
  12.250   1.2857   0.03266   0.02605  -0.0054   0.0136   1.0000
  12.500   1.2784   0.03542   0.02891  -0.0036   0.0132   1.0000
  12.750   1.2712   0.03842   0.03201  -0.0024   0.0131   1.0000
  13.000   1.2659   0.04146   0.03515  -0.0017   0.0130   1.0000
  13.250   1.2552   0.04522   0.03900  -0.0011   0.0128   1.0000
  13.500   1.2483   0.04869   0.04257  -0.0008   0.0125   1.0000
  13.750   1.2509   0.05138   0.04537  -0.0010   0.0123   1.0000
  14.000   1.2506   0.05435   0.04842  -0.0011   0.0122   1.0000
  14.250   1.2499   0.05740   0.05157  -0.0013   0.0121   1.0000
  14.500   1.2492   0.06047   0.05473  -0.0014   0.0119   1.0000
  14.750   1.2493   0.06342   0.05777  -0.0016   0.0118   1.0000
  15.000   1.2489   0.06642   0.06085  -0.0017   0.0116   1.0000
  15.250   1.2493   0.06922   0.06372  -0.0015   0.0116   1.0000
  15.500   1.2499   0.07219   0.06677  -0.0017   0.0114   1.0000
  15.750   1.2503   0.07515   0.06982  -0.0019   0.0113   1.0000
  16.000   1.2513   0.07797   0.07273  -0.0019   0.0112   1.0000
  16.250   1.2520   0.08091   0.07576  -0.0020   0.0111   1.0000
  16.500   1.2520   0.08404   0.07897  -0.0024   0.0109   1.0000
  16.750   1.2522   0.08707   0.08213  -0.0026   0.0110   1.0000
  17.000   1.2510   0.09043   0.08560  -0.0031   0.0109   1.0000
  17.250   1.2490   0.09401   0.08928  -0.0039   0.0108   1.0000
  17.500   1.2456   0.09784   0.09323  -0.0047   0.0107   1.0000
  17.750   1.2412   0.10197   0.09750  -0.0060   0.0108   1.0000
  18.000   1.2343   0.10655   0.10223  -0.0075   0.0109   1.0000
  18.250   1.2300   0.11076   0.10653  -0.0091   0.0106   1.0000
  18.500   1.2164   0.11686   0.11286  -0.0116   0.0110   1.0000
  18.750   1.2129   0.12114   0.11720  -0.0138   0.0106   1.0000
  19.000   1.1981   0.12777   0.12404  -0.0170   0.0108   1.0000
  19.250   1.1824   0.13476   0.13122  -0.0206   0.0110   1.0000
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