CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: CH10 (smoothed) (ch10sm-il) Reynolds number: 500,000 Max Cl/Cd: 132.36 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ch10sm-il-500000-n5.txt Download as CSV file: xf-ch10sm-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: CH10 (smoothed)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 0.2748 0.09398 0.09018 -0.1585 0.7621 0.0140
-9.500 0.2843 0.09155 0.08774 -0.1598 0.7582 0.0145
-9.000 0.2978 0.08511 0.08126 -0.1628 0.7513 0.0121
-8.750 0.3086 0.08303 0.07918 -0.1637 0.7476 0.0119
-8.500 0.3183 0.08070 0.07685 -0.1649 0.7436 0.0118
-8.250 0.3272 0.07817 0.07430 -0.1662 0.7399 0.0118
-8.000 0.3356 0.07550 0.07160 -0.1676 0.7365 0.0120
-7.750 0.3432 0.07255 0.06867 -0.1693 0.7331 0.0121
-7.500 0.3508 0.06975 0.06588 -0.1708 0.7294 0.0124
-7.250 0.3644 0.06855 0.06467 -0.1715 0.7258 0.0127
-7.000 0.3764 0.06701 0.06310 -0.1723 0.7223 0.0131
-6.750 0.3865 0.06511 0.06121 -0.1733 0.7188 0.0138
-6.500 0.3949 0.06296 0.05908 -0.1746 0.7152 0.0141
-5.500 0.5736 0.01728 0.01211 -0.2613 0.7021 0.0173
-5.250 0.6107 0.01528 0.00964 -0.2652 0.6988 0.0180
-5.000 0.6429 0.01431 0.00835 -0.2670 0.6957 0.0187
-4.750 0.6733 0.01369 0.00754 -0.2682 0.6927 0.0194
-4.500 0.7023 0.01339 0.00716 -0.2689 0.6898 0.0201
-4.250 0.7315 0.01301 0.00669 -0.2696 0.6866 0.0207
-4.000 0.7607 0.01264 0.00619 -0.2702 0.6834 0.0215
-3.750 0.7898 0.01231 0.00574 -0.2708 0.6803 0.0223
-3.500 0.8187 0.01204 0.00534 -0.2713 0.6772 0.0231
-3.250 0.8474 0.01183 0.00508 -0.2718 0.6744 0.0242
-3.000 0.8756 0.01170 0.00492 -0.2721 0.6712 0.0257
-2.750 0.9038 0.01157 0.00472 -0.2724 0.6681 0.0274
-2.500 0.9322 0.01142 0.00453 -0.2728 0.6649 0.0292
-2.250 0.9601 0.01136 0.00441 -0.2730 0.6619 0.0313
-2.000 0.9883 0.01128 0.00428 -0.2733 0.6590 0.0338
-1.750 1.0161 0.01123 0.00423 -0.2736 0.6560 0.0372
-1.500 1.0438 0.01119 0.00417 -0.2738 0.6529 0.0410
-1.250 1.0712 0.01117 0.00413 -0.2739 0.6496 0.0451
-1.000 1.0983 0.01118 0.00409 -0.2740 0.6466 0.0496
-0.750 1.1255 0.01119 0.00410 -0.2741 0.6437 0.0554
-0.500 1.1527 0.01118 0.00409 -0.2742 0.6407 0.0612
-0.250 1.1796 0.01119 0.00411 -0.2742 0.6374 0.0682
0.000 1.2062 0.01122 0.00413 -0.2742 0.6341 0.0766
0.250 1.2326 0.01127 0.00416 -0.2742 0.6310 0.0869
0.500 1.2593 0.01130 0.00422 -0.2742 0.6281 0.1036
1.000 1.3124 0.01129 0.00442 -0.2744 0.6214 0.1969
1.250 1.3385 0.01132 0.00454 -0.2744 0.6180 0.2572
1.500 1.3643 0.01138 0.00468 -0.2743 0.6149 0.3175
1.750 1.3900 0.01143 0.00484 -0.2742 0.6117 0.3741
2.000 1.4154 0.01148 0.00501 -0.2740 0.6082 0.4300
2.250 1.4402 0.01156 0.00518 -0.2738 0.6046 0.4865
2.500 1.4647 0.01164 0.00537 -0.2734 0.6012 0.5606
2.750 1.4891 0.01165 0.00560 -0.2731 0.5980 0.6755
3.000 1.5099 0.01141 0.00575 -0.2718 0.5946 1.0000
3.250 1.5327 0.01158 0.00591 -0.2711 0.5907 1.0000
3.500 1.5550 0.01178 0.00608 -0.2703 0.5869 1.0000
4.000 1.5992 0.01220 0.00647 -0.2686 0.5798 1.0000
4.250 1.6207 0.01242 0.00668 -0.2677 0.5757 1.0000
4.500 1.6412 0.01267 0.00692 -0.2666 0.5715 1.0000
4.750 1.6613 0.01295 0.00718 -0.2654 0.5677 1.0000
5.000 1.6820 0.01319 0.00745 -0.2644 0.5635 1.0000
5.250 1.7015 0.01348 0.00775 -0.2632 0.5589 1.0000
5.500 1.7199 0.01382 0.00807 -0.2618 0.5544 1.0000
5.750 1.7389 0.01415 0.00842 -0.2605 0.5501 1.0000
6.000 1.7576 0.01449 0.00879 -0.2592 0.5452 1.0000
6.250 1.7747 0.01490 0.00920 -0.2576 0.5403 1.0000
6.500 1.7921 0.01532 0.00963 -0.2562 0.5358 1.0000
6.750 1.8097 0.01574 0.01009 -0.2548 0.5306 1.0000
7.000 1.8252 0.01625 0.01061 -0.2530 0.5251 1.0000
7.250 1.8411 0.01677 0.01115 -0.2514 0.5200 1.0000
7.500 1.8570 0.01730 0.01173 -0.2498 0.5142 1.0000
7.750 1.8707 0.01794 0.01238 -0.2479 0.5085 1.0000
8.000 1.8858 0.01855 0.01302 -0.2462 0.5031 1.0000
8.250 1.9000 0.01921 0.01372 -0.2444 0.4971 1.0000
8.500 1.9116 0.02002 0.01453 -0.2423 0.4913 1.0000
8.750 1.9261 0.02070 0.01529 -0.2407 0.4853 1.0000
9.000 1.9370 0.02159 0.01620 -0.2385 0.4790 1.0000
9.250 1.9488 0.02246 0.01711 -0.2366 0.4729 1.0000
9.500 1.9594 0.02341 0.01810 -0.2345 0.4659 1.0000
9.750 1.9681 0.02449 0.01922 -0.2322 0.4594 1.0000
10.000 1.9749 0.02573 0.02048 -0.2297 0.4496 1.0000
10.250 1.9764 0.02738 0.02213 -0.2266 0.4363 1.0000
10.500 1.9733 0.02943 0.02414 -0.2230 0.4200 1.0000
10.750 1.9680 0.03173 0.02639 -0.2193 0.4029 1.0000
11.000 1.9627 0.03415 0.02877 -0.2158 0.3864 1.0000
11.500 1.9507 0.03940 0.03394 -0.2091 0.3527 1.0000
11.750 1.9423 0.04235 0.03684 -0.2058 0.3341 1.0000
12.000 1.9329 0.04550 0.03993 -0.2025 0.3156 1.0000
12.250 1.9232 0.04875 0.04313 -0.1993 0.2979 1.0000
12.500 1.9126 0.05216 0.04648 -0.1962 0.2804 1.0000
12.750 1.9026 0.05559 0.04986 -0.1933 0.2625 1.0000
13.000 1.8918 0.05919 0.05340 -0.1905 0.2434 1.0000
13.250 1.8788 0.06308 0.05720 -0.1877 0.2235 1.0000
13.500 1.8652 0.06711 0.06117 -0.1850 0.2034 1.0000
13.750 1.8504 0.07136 0.06533 -0.1824 0.1815 1.0000
14.000 1.8350 0.07578 0.06964 -0.1799 0.1587 1.0000
14.250 1.8181 0.08041 0.07416 -0.1776 0.1352 1.0000
14.500 1.8023 0.08500 0.07864 -0.1754 0.1124 1.0000
14.750 1.7845 0.08994 0.08346 -0.1734 0.0883 1.0000
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Polar data table (+)
Polar graphs
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