HT05 (ht05-il) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: HT05 (ht05-il) Reynolds number: 50,000 Max Cl/Cd: 19.62 at α=4.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ht05-il-50000-n5.txt Download as CSV file: xf-ht05-il-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: HT05
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.7287 0.10319 0.09624 0.0188 1.0000 0.0475
-8.750 -0.7259 0.09879 0.09186 0.0177 1.0000 0.0470
-8.500 -0.7259 0.09394 0.08705 0.0150 1.0000 0.0468
-8.250 -0.7248 0.08847 0.08159 0.0111 1.0000 0.0467
-8.000 -0.7225 0.08238 0.07547 0.0065 1.0000 0.0466
-7.750 -0.7197 0.07600 0.06900 0.0021 1.0000 0.0467
-7.500 -0.7160 0.06953 0.06235 -0.0019 1.0000 0.0469
-7.250 -0.7101 0.06331 0.05581 -0.0050 1.0000 0.0473
-7.000 -0.7014 0.05757 0.04974 -0.0070 1.0000 0.0478
-6.750 -0.6892 0.05266 0.04446 -0.0079 1.0000 0.0484
-6.500 -0.6743 0.04791 0.03929 -0.0085 1.0000 0.0489
-6.250 -0.6568 0.04378 0.03474 -0.0087 1.0000 0.0498
-6.000 -0.6372 0.04006 0.03057 -0.0087 1.0000 0.0512
-5.750 -0.6158 0.03706 0.02711 -0.0085 1.0000 0.0552
-5.500 -0.5921 0.03374 0.02296 -0.0080 1.0000 0.0596
-5.250 -0.5684 0.03097 0.01989 -0.0075 1.0000 0.0626
-5.000 -0.5436 0.02881 0.01743 -0.0069 1.0000 0.0670
-4.750 -0.5183 0.02698 0.01522 -0.0063 1.0000 0.0758
-4.500 -0.4927 0.02532 0.01333 -0.0056 1.0000 0.0844
-4.250 -0.4671 0.02381 0.01172 -0.0049 1.0000 0.0955
-4.000 -0.4408 0.02257 0.01031 -0.0043 1.0000 0.1141
-3.750 -0.4140 0.02135 0.00915 -0.0040 1.0000 0.1377
-3.500 -0.3877 0.02026 0.00807 -0.0036 1.0000 0.1739
-3.250 -0.3617 0.01925 0.00722 -0.0032 1.0000 0.2272
-3.000 -0.3366 0.01823 0.00654 -0.0028 1.0000 0.2970
-2.750 -0.3134 0.01719 0.00604 -0.0018 1.0000 0.3978
-2.500 -0.2928 0.01624 0.00567 0.0001 1.0000 0.5395
-2.250 -0.2709 0.01526 0.00508 0.0021 1.0000 0.6656
-2.000 -0.1971 0.01452 0.00467 -0.0056 1.0000 1.0000
-1.750 -0.1725 0.01443 0.00431 -0.0050 1.0000 1.0000
-1.500 -0.1478 0.01436 0.00399 -0.0043 1.0000 1.0000
-1.250 -0.1232 0.01430 0.00375 -0.0036 1.0000 1.0000
-1.000 -0.0986 0.01425 0.00356 -0.0029 1.0000 1.0000
-0.750 -0.0739 0.01422 0.00342 -0.0022 1.0000 1.0000
-0.500 -0.0493 0.01419 0.00331 -0.0014 1.0000 1.0000
-0.250 -0.0246 0.01418 0.00325 -0.0007 1.0000 1.0000
0.000 0.0001 0.01417 0.00323 0.0000 1.0000 1.0000
0.250 0.0247 0.01418 0.00325 0.0007 1.0000 1.0000
0.500 0.0494 0.01419 0.00331 0.0014 1.0000 1.0000
0.750 0.0740 0.01422 0.00342 0.0022 1.0000 1.0000
1.000 0.0987 0.01425 0.00356 0.0029 1.0000 1.0000
1.250 0.1233 0.01430 0.00375 0.0036 1.0000 1.0000
1.500 0.1480 0.01436 0.00399 0.0043 1.0000 1.0000
1.750 0.1726 0.01443 0.00431 0.0050 1.0000 1.0000
2.000 0.1972 0.01452 0.00467 0.0056 1.0000 1.0000
2.250 0.2710 0.01527 0.00508 -0.0021 0.6648 1.0000
2.500 0.2929 0.01625 0.00567 -0.0001 0.5387 1.0000
2.750 0.3135 0.01720 0.00604 0.0018 0.3972 1.0000
3.000 0.3367 0.01823 0.00654 0.0028 0.2967 1.0000
3.250 0.3619 0.01925 0.00723 0.0032 0.2270 1.0000
3.500 0.3878 0.02027 0.00808 0.0036 0.1739 1.0000
3.750 0.4141 0.02135 0.00915 0.0040 0.1374 1.0000
4.000 0.4409 0.02258 0.01033 0.0043 0.1140 1.0000
4.250 0.4672 0.02381 0.01173 0.0049 0.0953 1.0000
4.500 0.4928 0.02533 0.01335 0.0056 0.0844 1.0000
4.750 0.5184 0.02698 0.01520 0.0063 0.0757 1.0000
5.000 0.5437 0.02881 0.01744 0.0069 0.0670 1.0000
5.250 0.5685 0.03099 0.01990 0.0075 0.0626 1.0000
5.500 0.5923 0.03377 0.02302 0.0080 0.0596 1.0000
5.750 0.6159 0.03707 0.02712 0.0084 0.0551 1.0000
6.000 0.6374 0.04004 0.03055 0.0087 0.0512 1.0000
6.250 0.6570 0.04375 0.03469 0.0087 0.0498 1.0000
6.500 0.6745 0.04789 0.03926 0.0085 0.0489 1.0000
6.750 0.6893 0.05264 0.04443 0.0079 0.0484 1.0000
7.250 0.7100 0.06349 0.05602 0.0048 0.0473 1.0000
7.500 0.7158 0.06977 0.06260 0.0016 0.0469 1.0000
7.750 0.7195 0.07626 0.06927 -0.0024 0.0468 1.0000
8.000 0.7225 0.08263 0.07573 -0.0069 0.0467 1.0000
8.250 0.7249 0.08868 0.08181 -0.0115 0.0467 1.0000
8.500 0.7259 0.09411 0.08722 -0.0153 0.0469 1.0000
8.750 0.7261 0.09892 0.09199 -0.0179 0.0472 1.0000
9.000 0.7289 0.10332 0.09637 -0.0190 0.0476 1.0000
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Polar data table (+)
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