CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: CH10 (smoothed) (ch10sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 163.97 at α=3.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ch10sm-il-1000000-n5.txt Download as CSV file: xf-ch10sm-il-1000000-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 = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 0.2402 0.09742 0.09422 -0.1559 0.7408 0.0068
-10.250 0.2483 0.09461 0.09139 -0.1571 0.7372 0.0069
-9.750 0.2636 0.08849 0.08527 -0.1601 0.7305 0.0073
-7.750 0.3324 0.01694 0.01281 -0.2587 0.7025 0.0121
-7.500 0.3673 0.01515 0.01073 -0.2627 0.6992 0.0123
-7.250 0.3999 0.01393 0.00931 -0.2653 0.6961 0.0127
-7.000 0.4295 0.01339 0.00865 -0.2664 0.6929 0.0130
-6.750 0.4588 0.01297 0.00813 -0.2673 0.6899 0.0134
-6.500 0.4887 0.01252 0.00759 -0.2683 0.6870 0.0137
-6.250 0.5186 0.01204 0.00699 -0.2693 0.6838 0.0141
-6.000 0.5481 0.01161 0.00643 -0.2701 0.6806 0.0144
-5.750 0.5771 0.01125 0.00594 -0.2708 0.6775 0.0147
-5.500 0.6062 0.01094 0.00551 -0.2714 0.6745 0.0150
-5.250 0.6356 0.01065 0.00514 -0.2720 0.6716 0.0153
-5.000 0.6651 0.01030 0.00470 -0.2728 0.6684 0.0157
-4.750 0.6940 0.01007 0.00441 -0.2733 0.6652 0.0163
-4.500 0.7222 0.00994 0.00421 -0.2736 0.6620 0.0169
-4.250 0.7506 0.00981 0.00403 -0.2739 0.6591 0.0175
-4.000 0.7796 0.00966 0.00382 -0.2744 0.6563 0.0181
-3.750 0.8083 0.00952 0.00364 -0.2748 0.6533 0.0186
-3.500 0.8368 0.00939 0.00345 -0.2751 0.6501 0.0193
-3.250 0.8645 0.00930 0.00331 -0.2753 0.6468 0.0203
-3.000 0.8923 0.00924 0.00321 -0.2755 0.6439 0.0214
-2.750 0.9208 0.00916 0.00311 -0.2758 0.6413 0.0225
-2.500 0.9490 0.00909 0.00302 -0.2761 0.6383 0.0243
-2.250 0.9767 0.00906 0.00297 -0.2763 0.6351 0.0265
-2.000 1.0040 0.00904 0.00293 -0.2763 0.6318 0.0288
-1.750 1.0314 0.00904 0.00291 -0.2765 0.6289 0.0317
-1.500 1.0596 0.00901 0.00287 -0.2767 0.6263 0.0345
-1.250 1.0873 0.00901 0.00287 -0.2769 0.6232 0.0382
-1.000 1.1146 0.00902 0.00287 -0.2770 0.6198 0.0421
-0.750 1.1413 0.00905 0.00289 -0.2770 0.6165 0.0465
-0.500 1.1679 0.00909 0.00291 -0.2769 0.6135 0.0511
-0.250 1.1954 0.00910 0.00294 -0.2771 0.6107 0.0573
0.000 1.2224 0.00912 0.00297 -0.2772 0.6073 0.0637
0.250 1.2488 0.00916 0.00301 -0.2771 0.6039 0.0707
0.500 1.2747 0.00923 0.00307 -0.2769 0.6005 0.0815
0.750 1.3010 0.00927 0.00314 -0.2769 0.5974 0.0953
1.000 1.3278 0.00929 0.00321 -0.2770 0.5942 0.1174
1.250 1.3544 0.00930 0.00330 -0.2770 0.5907 0.1639
1.500 1.3801 0.00934 0.00342 -0.2769 0.5870 0.2172
1.750 1.4047 0.00942 0.00356 -0.2766 0.5835 0.2611
2.000 1.4309 0.00944 0.00367 -0.2766 0.5806 0.3107
2.250 1.4559 0.00949 0.00380 -0.2763 0.5769 0.3578
2.500 1.4796 0.00957 0.00395 -0.2758 0.5730 0.4017
2.750 1.5028 0.00968 0.00414 -0.2752 0.5692 0.4566
3.000 1.5279 0.00975 0.00432 -0.2750 0.5658 0.5248
3.500 1.5767 0.00990 0.00473 -0.2743 0.5577 0.6705
3.750 1.5971 0.00974 0.00499 -0.2731 0.5535 1.0000
4.000 1.6206 0.00991 0.00514 -0.2726 0.5497 1.0000
4.250 1.6430 0.01009 0.00532 -0.2718 0.5452 1.0000
4.500 1.6635 0.01035 0.00556 -0.2707 0.5403 1.0000
4.750 1.6843 0.01060 0.00579 -0.2697 0.5360 1.0000
5.000 1.7061 0.01081 0.00601 -0.2689 0.5314 1.0000
5.250 1.7261 0.01110 0.00629 -0.2677 0.5263 1.0000
5.500 1.7448 0.01143 0.00661 -0.2663 0.5215 1.0000
5.750 1.7657 0.01170 0.00689 -0.2654 0.5165 1.0000
6.000 1.7845 0.01205 0.00723 -0.2641 0.5108 1.0000
6.250 1.8020 0.01246 0.00763 -0.2626 0.5053 1.0000
6.500 1.8214 0.01281 0.00800 -0.2615 0.4996 1.0000
6.750 1.8378 0.01329 0.00847 -0.2599 0.4936 1.0000
7.000 1.8558 0.01371 0.00891 -0.2585 0.4884 1.0000
7.250 1.8732 0.01417 0.00937 -0.2572 0.4823 1.0000
7.500 1.8873 0.01480 0.01000 -0.2552 0.4764 1.0000
7.750 1.9055 0.01525 0.01047 -0.2540 0.4709 1.0000
8.000 1.9199 0.01589 0.01112 -0.2522 0.4644 1.0000
8.250 1.9345 0.01654 0.01178 -0.2505 0.4583 1.0000
8.500 1.9491 0.01721 0.01247 -0.2488 0.4516 1.0000
8.750 1.9609 0.01804 0.01330 -0.2467 0.4447 1.0000
9.000 1.9725 0.01891 0.01418 -0.2447 0.4354 1.0000
9.250 1.9766 0.02024 0.01546 -0.2415 0.4202 1.0000
9.500 1.9744 0.02201 0.01715 -0.2376 0.4010 1.0000
9.750 1.9730 0.02383 0.01889 -0.2339 0.3815 1.0000
10.000 1.9721 0.02567 0.02068 -0.2305 0.3637 1.0000
10.250 1.9694 0.02773 0.02267 -0.2269 0.3454 1.0000
10.500 1.9634 0.03012 0.02497 -0.2231 0.3258 1.0000
10.750 1.9562 0.03267 0.02744 -0.2192 0.3050 1.0000
11.000 1.9485 0.03538 0.03006 -0.2155 0.2843 1.0000
11.250 1.9407 0.03820 0.03279 -0.2120 0.2656 1.0000
11.500 1.9333 0.04104 0.03556 -0.2086 0.2466 1.0000
11.750 1.9252 0.04401 0.03847 -0.2054 0.2274 1.0000
12.000 1.9144 0.04732 0.04169 -0.2020 0.2076 1.0000
12.250 1.9018 0.05089 0.04515 -0.1986 0.1845 1.0000
12.500 1.8871 0.05472 0.04887 -0.1952 0.1615 1.0000
12.750 1.8709 0.05883 0.05285 -0.1919 0.1373 1.0000
13.000 1.8551 0.06301 0.05691 -0.1888 0.1135 1.0000
13.250 1.8343 0.06779 0.06156 -0.1855 0.0862 1.0000
13.500 1.8216 0.07186 0.06556 -0.1830 0.0679 1.0000
13.750 1.8124 0.07562 0.06928 -0.1809 0.0536 1.0000
14.000 1.8064 0.07904 0.07267 -0.1791 0.0424 1.0000
14.250 1.8015 0.08236 0.07599 -0.1775 0.0340 1.0000
14.500 1.7981 0.08556 0.07920 -0.1760 0.0277 1.0000
14.750 1.7968 0.08854 0.08219 -0.1748 0.0230 1.0000
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Polar data table (+)
Polar graphs
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