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