XFOIL Version 6.94 Calculated polar for: S 4110-084-84,61 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.4126 0.00712 0.00276 -0.0935 0.8524 1.0000 0.500 0.4656 0.00717 0.00264 -0.0923 0.8284 1.0000 1.000 0.5190 0.00725 0.00255 -0.0911 0.8031 1.0000 1.500 0.5720 0.00736 0.00253 -0.0900 0.7744 1.0000 2.000 0.6249 0.00751 0.00255 -0.0888 0.7419 1.0000 2.500 0.6771 0.00771 0.00259 -0.0875 0.7036 1.0000 3.000 0.7286 0.00798 0.00273 -0.0862 0.6585 1.0000 3.500 0.7790 0.00837 0.00292 -0.0847 0.6047 1.0000 4.000 0.8272 0.00893 0.00322 -0.0829 0.5361 1.0000 4.500 0.8738 0.00968 0.00365 -0.0809 0.4565 1.0000 5.500 0.9628 0.01176 0.00498 -0.0770 0.2882 1.0000 6.000 1.0072 0.01291 0.00582 -0.0752 0.2222 1.0000 6.500 1.0519 0.01405 0.00677 -0.0735 0.1739 1.0000 7.000 1.0960 0.01522 0.00781 -0.0716 0.1407 1.0000 7.500 1.1406 0.01630 0.00888 -0.0699 0.1145 1.0000 8.000 1.1823 0.01764 0.01022 -0.0677 0.0924 1.0000 8.500 1.2232 0.01897 0.01161 -0.0654 0.0738 1.0000 9.500 1.2956 0.02225 0.01506 -0.0597 0.0482 1.0000 10.000 1.3216 0.02462 0.01754 -0.0556 0.0401 1.0000 10.500 1.3489 0.02625 0.01935 -0.0516 0.0338 1.0000 12.000 1.3849 0.03613 0.02992 -0.0374 0.0228 1.0000 12.500 1.3877 0.04098 0.03519 -0.0336 0.0211 1.0000 13.000 1.3900 0.04549 0.04006 -0.0310 0.0194 1.0000 13.500 1.3848 0.05134 0.04626 -0.0294 0.0183 1.0000 14.000 1.3736 0.05841 0.05366 -0.0294 0.0174 1.0000 14.500 1.3556 0.06726 0.06284 -0.0313 0.0169 1.0000 15.000 1.3294 0.07846 0.07441 -0.0356 0.0166 1.0000 15.500 1.2957 0.09260 0.08895 -0.0430 0.0165 1.0000 16.000 1.2536 0.11058 0.10736 -0.0540 0.0166 1.0000 18.000 0.8278 0.21616 0.21400 -0.1112 0.0319 1.0000 18.500 0.8385 0.22696 0.22484 -0.1136 0.0306 1.0000 19.000 0.8426 0.23648 0.23436 -0.1183 0.0303 1.0000 19.500 0.8410 0.24549 0.24338 -0.1249 0.0257 1.0000 20.000 0.8507 0.25328 0.25120 -0.1280 0.0239 1.0000 20.500 0.8683 0.26062 0.25858 -0.1288 0.0223 1.0000 21.000 0.8733 0.27225 0.27020 -0.1330 0.0219 1.0000 21.500 0.8753 0.28142 0.27938 -0.1382 0.0215 1.0000 22.000 0.8807 0.29076 0.28873 -0.1429 0.0199 1.0000 22.500 0.8887 0.29990 0.29790 -0.1464 0.0179 1.0000 23.000 0.8979 0.30784 0.30589 -0.1493 0.0164 1.0000 23.500 0.9102 0.31848 0.31655 -0.1509 0.0154 1.0000 24.000 0.9153 0.32781 0.32590 -0.1549 0.0153 1.0000 24.500 0.9193 0.33738 0.33549 -0.1593 0.0151 1.0000 25.000 0.9250 0.34773 0.34586 -0.1635 0.0133 1.0000 25.500 0.9319 0.35721 0.35536 -0.1668 0.0119 1.0000 26.000 0.9386 0.36624 0.36442 -0.1699 0.0113 1.0000 27.000 0.9540 0.38677 0.38502 -0.1749 0.0106 1.0000