CH10 (smoothed) (ch10sm-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: CH10 (smoothed) (ch10sm-il) Reynolds number: 200,000 Max Cl/Cd: 86.22 at α=3.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ch10sm-il-200000-n5.txt Download as CSV file: xf-ch10sm-il-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.000 0.2241 0.11034 0.10559 -0.1540 0.8300 0.0228
-10.750 0.2313 0.10813 0.10338 -0.1554 0.8258 0.0229
-10.500 0.2386 0.10582 0.10107 -0.1567 0.8212 0.0229
-10.250 0.2514 0.10258 0.09781 -0.1567 0.8175 0.0232
-10.000 0.2622 0.10013 0.09532 -0.1574 0.8141 0.0236
-9.750 0.2718 0.09791 0.09310 -0.1582 0.8098 0.0240
-9.500 0.2811 0.09572 0.09090 -0.1591 0.8053 0.0246
-9.250 0.2906 0.09347 0.08862 -0.1601 0.8015 0.0252
-9.000 0.3005 0.09116 0.08627 -0.1614 0.7983 0.0260
-8.750 0.3084 0.08899 0.08413 -0.1627 0.7937 0.0270
-8.500 0.3143 0.08702 0.08216 -0.1646 0.7891 0.0274
-8.250 0.3174 0.08534 0.08047 -0.1673 0.7849 0.0276
-8.000 0.3357 0.08207 0.07715 -0.1660 0.7824 0.0284
-7.750 0.3455 0.08017 0.07528 -0.1663 0.7780 0.0293
-7.500 0.3549 0.07815 0.07326 -0.1671 0.7739 0.0301
-7.250 0.3645 0.07604 0.07113 -0.1682 0.7702 0.0309
-7.000 0.3740 0.07389 0.06894 -0.1695 0.7669 0.0319
-6.750 0.3774 0.07220 0.06730 -0.1707 0.7619 0.0327
-6.500 0.3826 0.07042 0.06554 -0.1728 0.7576 0.0330
-6.250 0.3953 0.06791 0.06301 -0.1763 0.7542 0.0331
-6.000 0.4101 0.06524 0.06031 -0.1795 0.7509 0.0331
-5.750 0.4227 0.06278 0.05787 -0.1816 0.7465 0.0331
-5.500 0.4403 0.05984 0.05491 -0.1860 0.7425 0.0332
-5.250 0.4476 0.05932 0.05440 -0.1798 0.7398 0.0355
-4.750 0.4924 0.05086 0.04584 -0.1936 0.7327 0.0273
-4.500 0.5147 0.04817 0.04312 -0.1976 0.7288 0.0269
-4.250 0.5478 0.04436 0.03924 -0.2052 0.7255 0.0267
-3.750 0.7185 0.02413 0.01774 -0.2536 0.7211 0.0288
-3.500 0.7581 0.02172 0.01487 -0.2583 0.7175 0.0300
-3.250 0.7957 0.01996 0.01254 -0.2616 0.7141 0.0327
-3.000 0.8285 0.01901 0.01133 -0.2634 0.7109 0.0342
-2.750 0.8604 0.01845 0.01058 -0.2647 0.7082 0.0358
-2.500 0.8938 0.01783 0.00971 -0.2662 0.7059 0.0380
-2.250 0.9197 0.01751 0.00929 -0.2662 0.7021 0.0410
-2.000 0.9465 0.01736 0.00911 -0.2664 0.6984 0.0441
-1.750 0.9757 0.01706 0.00867 -0.2669 0.6953 0.0477
-1.500 1.0057 0.01685 0.00842 -0.2676 0.6927 0.0524
-1.250 1.0359 0.01670 0.00816 -0.2683 0.6902 0.0579
-1.000 1.0603 0.01665 0.00815 -0.2680 0.6862 0.0638
-0.750 1.0865 0.01662 0.00807 -0.2680 0.6827 0.0702
-0.500 1.1148 0.01652 0.00798 -0.2684 0.6796 0.0787
-0.250 1.1445 0.01644 0.00784 -0.2690 0.6770 0.0885
0.000 1.1729 0.01643 0.00779 -0.2694 0.6742 0.1014
0.250 1.1966 0.01649 0.00793 -0.2690 0.6702 0.1201
0.500 1.2227 0.01650 0.00804 -0.2690 0.6668 0.1591
0.750 1.2505 0.01644 0.00816 -0.2694 0.6638 0.2453
1.000 1.2799 0.01639 0.00824 -0.2701 0.6611 0.3364
1.250 1.3051 0.01647 0.00847 -0.2699 0.6578 0.4133
1.500 1.3279 0.01662 0.00878 -0.2693 0.6539 0.4855
1.750 1.3529 0.01671 0.00899 -0.2690 0.6505 0.5614
2.000 1.3790 0.01662 0.00913 -0.2689 0.6475 0.6943
2.250 1.4021 0.01635 0.00904 -0.2679 0.6449 1.0000
2.500 1.4215 0.01670 0.00938 -0.2666 0.6408 1.0000
2.750 1.4433 0.01698 0.00963 -0.2657 0.6368 1.0000
3.000 1.4675 0.01719 0.00979 -0.2653 0.6334 1.0000
3.250 1.4951 0.01734 0.00985 -0.2655 0.6305 1.0000
3.500 1.5166 0.01764 0.01014 -0.2646 0.6269 1.0000
3.750 1.5345 0.01800 0.01052 -0.2631 0.6226 1.0000
4.000 1.5553 0.01827 0.01078 -0.2621 0.6188 1.0000
4.250 1.5810 0.01845 0.01090 -0.2619 0.6158 1.0000
4.500 1.6023 0.01874 0.01118 -0.2610 0.6122 1.0000
4.750 1.6153 0.01921 0.01170 -0.2586 0.6075 1.0000
5.000 1.6341 0.01954 0.01206 -0.2573 0.6035 1.0000
5.250 1.6591 0.01973 0.01221 -0.2570 0.6002 1.0000
5.500 1.6757 0.02015 0.01266 -0.2553 0.5961 1.0000
5.750 1.6869 0.02072 0.01330 -0.2527 0.5911 1.0000
6.000 1.7057 0.02108 0.01368 -0.2514 0.5869 1.0000
6.250 1.7322 0.02121 0.01377 -0.2515 0.5836 1.0000
6.500 1.7364 0.02208 0.01475 -0.2478 0.5779 1.0000
6.750 1.7501 0.02264 0.01536 -0.2458 0.5730 1.0000
7.000 1.7734 0.02286 0.01557 -0.2453 0.5692 1.0000
7.250 1.7806 0.02373 0.01654 -0.2424 0.5636 1.0000
7.500 1.7911 0.02448 0.01736 -0.2400 0.5582 1.0000
7.750 1.8126 0.02477 0.01764 -0.2392 0.5540 1.0000
8.000 1.8182 0.02581 0.01880 -0.2362 0.5481 1.0000
8.250 1.8281 0.02667 0.01973 -0.2339 0.5424 1.0000
8.500 1.8498 0.02693 0.01998 -0.2332 0.5380 1.0000
8.750 1.8489 0.02845 0.02163 -0.2295 0.5310 1.0000
9.000 1.8618 0.02920 0.02243 -0.2277 0.5253 1.0000
9.250 1.8733 0.03007 0.02337 -0.2257 0.5197 1.0000
9.500 1.8766 0.03148 0.02489 -0.2228 0.5128 1.0000
9.750 1.8941 0.03197 0.02539 -0.2216 0.5076 1.0000
10.000 1.8926 0.03378 0.02734 -0.2183 0.5003 1.0000
10.250 1.9040 0.03470 0.02832 -0.2165 0.4941 1.0000
10.500 1.9085 0.03618 0.02990 -0.2139 0.4873 1.0000
10.750 1.9146 0.03755 0.03134 -0.2116 0.4803 1.0000
11.000 1.9225 0.03881 0.03267 -0.2096 0.4736 1.0000
11.250 1.9249 0.04057 0.03453 -0.2071 0.4659 1.0000
11.500 1.9336 0.04181 0.03584 -0.2052 0.4590 1.0000
11.750 1.9334 0.04384 0.03796 -0.2025 0.4494 1.0000
12.000 1.9313 0.04609 0.04026 -0.1998 0.4383 1.0000
12.250 1.9288 0.04838 0.04258 -0.1971 0.4251 1.0000
12.500 1.9238 0.05099 0.04519 -0.1943 0.4099 1.0000
12.750 1.9176 0.05381 0.04800 -0.1915 0.3937 1.0000
13.000 1.9107 0.05678 0.05094 -0.1888 0.3767 1.0000
13.250 1.9030 0.05990 0.05404 -0.1862 0.3595 1.0000
13.500 1.8948 0.06316 0.05726 -0.1837 0.3424 1.0000
13.750 1.8857 0.06658 0.06065 -0.1812 0.3254 1.0000
14.000 1.8760 0.07019 0.06422 -0.1789 0.3080 1.0000
14.250 1.8654 0.07394 0.06795 -0.1767 0.2900 1.0000
14.500 1.8530 0.07798 0.07194 -0.1746 0.2713 1.0000
14.750 1.8392 0.08230 0.07620 -0.1726 0.2523 1.0000
15.000 1.8260 0.08662 0.08047 -0.1708 0.2339 1.0000
15.250 1.8134 0.09093 0.08474 -0.1691 0.2151 1.0000
15.500 1.7997 0.09545 0.08921 -0.1677 0.1959 1.0000
15.750 1.7849 0.10018 0.09388 -0.1664 0.1755 1.0000
16.000 1.7677 0.10534 0.09893 -0.1652 0.1525 1.0000
16.250 1.7496 0.11069 0.10417 -0.1644 0.1276 1.0000
16.500 1.7307 0.11616 0.10951 -0.1637 0.1029 1.0000
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