HT23 (ht23-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: HT23 (ht23-il) Reynolds number: 50,000 Max Cl/Cd: 24.41 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ht23-il-50000.txt Download as CSV file: xf-ht23-il-50000.csv |
XFOIL Version 6.96
Calculated polar for: HT23
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.6639 0.13070 0.12398 0.0428 1.0000 0.1801
-9.250 -0.6498 0.12606 0.11932 0.0437 1.0000 0.1889
-9.000 -0.6706 0.12557 0.11896 0.0386 1.0000 0.1931
-8.750 -0.6429 0.11881 0.11216 0.0419 1.0000 0.2034
-8.500 -0.6477 0.11571 0.10915 0.0396 1.0000 0.2095
-8.250 -0.6416 0.11219 0.10564 0.0394 1.0000 0.2202
-8.000 -0.6314 0.10772 0.10120 0.0397 1.0000 0.2286
-7.750 -0.6451 0.10560 0.09922 0.0360 1.0000 0.2375
-7.500 -0.6381 0.10194 0.09558 0.0361 1.0000 0.2504
-7.250 -0.6256 0.09756 0.09123 0.0372 1.0000 0.2633
-7.000 -0.6221 0.09408 0.08781 0.0368 1.0000 0.2781
-6.750 -0.6265 0.09121 0.08502 0.0329 1.0000 0.2950
-6.500 -0.6056 0.08655 0.08038 0.0380 1.0000 0.3155
-6.000 -0.5899 0.07971 0.07365 0.0395 1.0000 0.3639
-5.750 -0.5801 0.07613 0.07010 0.0410 1.0000 0.3895
-5.500 -0.5701 0.07274 0.06676 0.0428 1.0000 0.4190
-5.250 -0.5651 0.06987 0.06396 0.0448 1.0000 0.4578
-5.000 -0.4920 0.04701 0.03917 -0.0122 1.0000 0.1473
-4.750 -0.4636 0.04140 0.03298 -0.0142 1.0000 0.1290
-4.500 -0.4336 0.03682 0.02755 -0.0153 1.0000 0.1188
-4.250 -0.4057 0.03345 0.02361 -0.0155 1.0000 0.1187
-4.000 -0.3764 0.03065 0.02012 -0.0153 1.0000 0.1211
-3.750 -0.3483 0.02776 0.01703 -0.0150 1.0000 0.1242
-3.500 -0.3196 0.02566 0.01464 -0.0144 1.0000 0.1334
-3.250 -0.2912 0.02363 0.01248 -0.0137 1.0000 0.1475
-3.000 -0.2633 0.02172 0.01063 -0.0129 1.0000 0.1724
-2.750 -0.2353 0.01976 0.00891 -0.0120 1.0000 0.2255
-2.500 -0.1859 0.01442 0.00693 -0.0105 1.0000 1.0000
-2.250 -0.1608 0.01426 0.00616 -0.0102 1.0000 1.0000
-2.000 -0.1357 0.01413 0.00558 -0.0098 1.0000 1.0000
-1.750 -0.1104 0.01403 0.00514 -0.0094 1.0000 1.0000
-1.500 -0.0850 0.01396 0.00478 -0.0090 1.0000 1.0000
-1.250 -0.0595 0.01390 0.00449 -0.0087 1.0000 1.0000
-1.000 -0.0339 0.01386 0.00425 -0.0083 1.0000 1.0000
-0.750 -0.0083 0.01384 0.00407 -0.0080 1.0000 1.0000
-0.500 0.0173 0.01383 0.00396 -0.0076 1.0000 1.0000
-0.250 0.0429 0.01384 0.00388 -0.0073 1.0000 1.0000
0.000 0.0684 0.01387 0.00386 -0.0070 1.0000 1.0000
0.250 0.0937 0.01392 0.00390 -0.0068 1.0000 1.0000
0.500 0.1187 0.01399 0.00401 -0.0066 1.0000 1.0000
0.750 0.1432 0.01410 0.00419 -0.0064 1.0000 1.0000
1.000 0.1662 0.01429 0.00451 -0.0065 1.0000 1.0000
1.250 0.1842 0.01476 0.00514 -0.0069 1.0000 1.0000
1.500 0.2695 0.01556 0.00617 -0.0208 0.9380 1.0000
1.750 0.3300 0.01594 0.00652 -0.0253 0.8460 1.0000
2.000 0.3530 0.01652 0.00687 -0.0224 0.7836 1.0000
2.250 0.3735 0.01717 0.00733 -0.0195 0.7335 1.0000
2.500 0.3953 0.01785 0.00783 -0.0172 0.6897 1.0000
2.750 0.4183 0.01856 0.00840 -0.0154 0.6500 1.0000
3.000 0.4421 0.01930 0.00906 -0.0139 0.6131 1.0000
3.250 0.4660 0.02007 0.00975 -0.0125 0.5789 1.0000
3.500 0.4902 0.02087 0.01050 -0.0112 0.5468 1.0000
3.750 0.5148 0.02170 0.01126 -0.0099 0.5156 1.0000
4.000 0.5396 0.02258 0.01215 -0.0090 0.4835 1.0000
4.250 0.5643 0.02348 0.01306 -0.0079 0.4523 1.0000
4.500 0.5889 0.02440 0.01403 -0.0069 0.4211 1.0000
4.750 0.6133 0.02532 0.01495 -0.0057 0.3895 1.0000
5.000 0.6373 0.02619 0.01578 -0.0045 0.3575 1.0000
5.250 0.6612 0.02709 0.01658 -0.0032 0.3251 1.0000
5.500 0.6852 0.02820 0.01784 -0.0023 0.2898 1.0000
5.750 0.7090 0.02930 0.01889 -0.0011 0.2573 1.0000
6.000 0.7328 0.03064 0.02022 -0.0002 0.2278 1.0000
6.250 0.7564 0.03243 0.02217 0.0005 0.2022 1.0000
6.500 0.7803 0.03453 0.02436 0.0012 0.1845 1.0000
6.750 0.8033 0.03694 0.02694 0.0017 0.1697 1.0000
7.000 0.8242 0.04021 0.03074 0.0017 0.1579 1.0000
7.250 0.8426 0.04475 0.03581 0.0013 0.1526 1.0000
7.500 0.8548 0.05060 0.04238 -0.0003 0.1484 1.0000
7.750 0.8741 0.05313 0.04489 0.0004 0.1406 1.0000
8.000 0.8785 0.06017 0.05249 -0.0021 0.1404 1.0000
8.250 0.8815 0.06721 0.05989 -0.0048 0.1420 1.0000
8.500 0.8288 0.08766 0.08071 -0.0262 0.1650 1.0000
8.750 0.8417 0.09256 0.08567 -0.0254 0.1694 1.0000
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Polar data table (+)
Polar graphs
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