CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: CH10 (smoothed) (ch10sm-il) Reynolds number: 200,000 Max Cl/Cd: 73.16 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ch10sm-il-200000.txt Download as CSV file: xf-ch10sm-il-200000.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 = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.2781 0.10238 0.09810 -0.1646 0.8691 0.0325
-9.750 0.2819 0.10141 0.09713 -0.1666 0.8639 0.0330
-9.500 0.2843 0.10066 0.09635 -0.1694 0.8599 0.0332
-9.250 0.2971 0.09651 0.09222 -0.1686 0.8553 0.0335
-9.000 0.3099 0.09340 0.08909 -0.1680 0.8510 0.0341
-8.750 0.3211 0.09106 0.08673 -0.1685 0.8473 0.0349
-8.500 0.3329 0.08877 0.08439 -0.1697 0.8443 0.0360
-8.250 0.3385 0.08718 0.08285 -0.1697 0.8386 0.0373
-8.000 0.3450 0.08569 0.08135 -0.1712 0.8336 0.0392
-7.750 0.3449 0.08559 0.08124 -0.1753 0.8291 0.0399
-7.500 0.3390 0.08536 0.08109 -0.1750 0.8218 0.0400
-7.250 0.3641 0.07962 0.07531 -0.1732 0.8201 0.0409
-7.000 0.3773 0.07722 0.07288 -0.1733 0.8169 0.0418
-6.750 0.3904 0.07502 0.07064 -0.1744 0.8141 0.0430
-6.500 0.3908 0.07400 0.06967 -0.1730 0.8081 0.0441
-6.250 0.3944 0.07268 0.06836 -0.1728 0.8033 0.0455
-6.000 0.4087 0.07141 0.06707 -0.1799 0.7996 0.0478
-5.750 0.4201 0.07039 0.06608 -0.1869 0.7933 0.0483
-5.500 0.4214 0.06728 0.06300 -0.1827 0.7892 0.0489
-5.250 0.4342 0.06488 0.06058 -0.1802 0.7865 0.0501
-5.000 0.4546 0.06266 0.05830 -0.1817 0.7842 0.0526
-4.750 0.4636 0.06133 0.05699 -0.1828 0.7794 0.0551
-4.250 0.5174 0.05522 0.05081 -0.1985 0.7707 0.0598
-4.000 0.5385 0.05307 0.04862 -0.1984 0.7688 0.0615
-3.750 0.5447 0.05211 0.04769 -0.1973 0.7634 0.0633
-3.500 0.6218 0.04615 0.04147 -0.2207 0.7590 0.0717
-3.250 0.6311 0.04494 0.04032 -0.2169 0.7562 0.0735
-3.000 0.6640 0.04303 0.03834 -0.2196 0.7544 0.0784
-2.750 0.7431 0.03756 0.03253 -0.2372 0.7530 0.0887
-2.500 0.7500 0.03721 0.03223 -0.2349 0.7472 0.0915
-2.250 0.8578 0.02837 0.02224 -0.2575 0.7454 0.0732
-2.000 0.9068 0.02536 0.01868 -0.2628 0.7428 0.0646
-1.750 0.9497 0.02379 0.01664 -0.2662 0.7407 0.0668
-1.500 0.9901 0.02279 0.01522 -0.2687 0.7388 0.0716
-1.250 1.0285 0.02182 0.01413 -0.2712 0.7371 0.0782
-1.000 1.0390 0.02238 0.01467 -0.2684 0.7311 0.0837
-0.750 1.0684 0.02189 0.01414 -0.2690 0.7276 0.0918
-0.500 1.1023 0.02147 0.01360 -0.2703 0.7252 0.1019
-0.250 1.1379 0.02099 0.01308 -0.2720 0.7232 0.1164
0.000 1.1750 0.02055 0.01264 -0.2739 0.7215 0.1360
0.250 1.1822 0.02129 0.01354 -0.2707 0.7150 0.1526
0.500 1.2127 0.02101 0.01353 -0.2717 0.7117 0.2312
0.750 1.2469 0.02059 0.01357 -0.2732 0.7094 0.4472
1.000 1.2810 0.02033 0.01347 -0.2745 0.7074 0.5681
1.250 1.3018 0.02054 0.01391 -0.2734 0.7037 0.6791
1.500 1.3096 0.02072 0.01445 -0.2697 0.6983 1.0000
1.750 1.3395 0.02080 0.01438 -0.2703 0.6954 1.0000
2.000 1.3733 0.02074 0.01418 -0.2716 0.6932 1.0000
2.250 1.4092 0.02064 0.01392 -0.2732 0.6912 1.0000
2.500 1.4133 0.02171 0.01506 -0.2694 0.6849 1.0000
2.750 1.4379 0.02196 0.01526 -0.2691 0.6812 1.0000
3.000 1.4705 0.02190 0.01511 -0.2701 0.6787 1.0000
3.250 1.5059 0.02177 0.01488 -0.2716 0.6766 1.0000
3.500 1.5176 0.02257 0.01571 -0.2691 0.6717 1.0000
3.750 1.5330 0.02314 0.01630 -0.2672 0.6668 1.0000
4.000 1.5642 0.02310 0.01622 -0.2680 0.6640 1.0000
4.250 1.5999 0.02293 0.01598 -0.2696 0.6618 1.0000
4.500 1.6237 0.02327 0.01631 -0.2692 0.6583 1.0000
4.750 1.6246 0.02430 0.01744 -0.2648 0.6519 1.0000
5.000 1.6551 0.02427 0.01740 -0.2655 0.6489 1.0000
5.250 1.6921 0.02403 0.01710 -0.2673 0.6465 1.0000
5.500 1.7118 0.02447 0.01756 -0.2662 0.6425 1.0000
5.750 1.7118 0.02546 0.01868 -0.2617 0.6362 1.0000
6.000 1.7442 0.02533 0.01852 -0.2627 0.6331 1.0000
6.250 1.7844 0.02498 0.01813 -0.2651 0.6307 1.0000
6.500 1.7766 0.02621 0.01949 -0.2591 0.6242 1.0000
6.750 1.7929 0.02656 0.01990 -0.2573 0.6195 1.0000
7.000 1.8311 0.02622 0.01955 -0.2594 0.6166 1.0000
7.250 1.8803 0.02570 0.01899 -0.2634 0.6142 1.0000
7.500 1.8410 0.02778 0.02126 -0.2521 0.6057 1.0000
7.750 1.8739 0.02753 0.02104 -0.2531 0.6022 1.0000
8.000 1.9243 0.02684 0.02032 -0.2572 0.5995 1.0000
8.250 1.8875 0.02904 0.02269 -0.2467 0.5912 1.0000
8.500 1.9164 0.02887 0.02256 -0.2470 0.5871 1.0000
8.750 1.9681 0.02799 0.02168 -0.2512 0.5843 1.0000
9.000 1.9285 0.03055 0.02441 -0.2407 0.5757 1.0000
9.250 1.9594 0.03026 0.02416 -0.2413 0.5715 1.0000
9.500 2.0135 0.02920 0.02311 -0.2456 0.5685 1.0000
9.750 1.9645 0.03238 0.02649 -0.2342 0.5591 1.0000
10.000 2.0044 0.03163 0.02577 -0.2361 0.5552 1.0000
10.250 1.9946 0.03338 0.02763 -0.2309 0.5481 1.0000
10.500 2.0048 0.03408 0.02841 -0.2286 0.5418 1.0000
10.750 2.0577 0.03261 0.02696 -0.2322 0.5380 1.0000
11.000 2.0126 0.03635 0.03089 -0.2226 0.5282 1.0000
11.250 2.0501 0.03515 0.02966 -0.2236 0.5210 1.0000
11.500 2.0295 0.03764 0.03228 -0.2176 0.5110 1.0000
11.750 2.0219 0.03942 0.03412 -0.2133 0.5007 1.0000
12.000 2.0292 0.04004 0.03474 -0.2107 0.4892 1.0000
12.250 2.0294 0.04137 0.03610 -0.2075 0.4774 1.0000
12.500 2.0089 0.04471 0.03956 -0.2026 0.4659 1.0000
12.750 2.0026 0.04700 0.04190 -0.1993 0.4538 1.0000
13.000 2.0005 0.04903 0.04397 -0.1965 0.4414 1.0000
13.250 1.9987 0.05113 0.04608 -0.1938 0.4285 1.0000
13.500 1.9940 0.05360 0.04856 -0.1910 0.4148 1.0000
13.750 1.9861 0.05650 0.05148 -0.1882 0.4006 1.0000
14.000 1.9763 0.05975 0.05475 -0.1854 0.3857 1.0000
14.250 1.9668 0.06305 0.05807 -0.1828 0.3704 1.0000
14.500 1.9569 0.06649 0.06152 -0.1803 0.3549 1.0000
14.750 1.9461 0.07014 0.06519 -0.1779 0.3391 1.0000
15.000 1.9344 0.07396 0.06902 -0.1756 0.3228 1.0000
15.250 1.9215 0.07802 0.07309 -0.1735 0.3054 1.0000
15.500 1.9072 0.08233 0.07737 -0.1714 0.2866 1.0000
15.750 1.8904 0.08701 0.08199 -0.1694 0.2666 1.0000
16.000 1.8716 0.09204 0.08697 -0.1676 0.2442 1.0000
16.250 1.8493 0.09763 0.09244 -0.1659 0.2202 1.0000
16.500 1.8246 0.10366 0.09834 -0.1645 0.1928 1.0000
16.750 1.7973 0.11021 0.10470 -0.1635 0.1603 1.0000
17.000 1.7683 0.11708 0.11134 -0.1628 0.1273 1.0000
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