XFOIL Version 6.94 Calculated polar for: AH 81-K-144/17 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3577 0.01193 0.00729 -0.0750 0.7058 0.8893 0.500 0.4115 0.01183 0.00711 -0.0743 0.7033 0.9067 1.000 0.4575 0.01203 0.00737 -0.0724 0.6986 0.9256 1.500 0.5164 0.01192 0.00726 -0.0728 0.6946 0.9472 2.000 0.5884 0.01170 0.00700 -0.0762 0.6920 0.9577 2.500 0.6558 0.01182 0.00715 -0.0793 0.6871 0.9653 3.000 0.7250 0.01177 0.00712 -0.0827 0.6828 0.9703 3.500 0.8000 0.01153 0.00686 -0.0870 0.6799 0.9731 4.000 0.8670 0.01155 0.00699 -0.0902 0.6729 0.9771 4.500 0.9364 0.01121 0.00667 -0.0933 0.6687 0.9804 5.000 1.0032 0.01112 0.00671 -0.0963 0.6607 0.9838 5.500 1.0702 0.01069 0.00638 -0.0990 0.6510 0.9879 6.000 1.1353 0.01025 0.00604 -0.1012 0.6374 0.9928 6.500 1.1950 0.00977 0.00558 -0.1024 0.6008 1.0000 7.000 1.2095 0.00994 0.00575 -0.0947 0.5679 1.0000 7.500 1.2263 0.01082 0.00636 -0.0880 0.5032 1.0000 8.000 1.2199 0.01293 0.00806 -0.0784 0.4219 1.0000 8.500 1.2033 0.01738 0.01202 -0.0718 0.3263 1.0000 9.000 1.1711 0.02329 0.01710 -0.0644 0.1918 1.0000 9.500 1.1599 0.02789 0.02111 -0.0591 0.0909 1.0000 10.000 1.1589 0.03199 0.02488 -0.0548 0.0405 1.0000 10.500 1.1742 0.03509 0.02802 -0.0521 0.0316 1.0000 11.000 1.1909 0.03828 0.03129 -0.0499 0.0259 1.0000 11.500 1.2041 0.04191 0.03502 -0.0477 0.0239 1.0000 12.000 1.2156 0.04579 0.03904 -0.0455 0.0219 1.0000 12.500 1.2269 0.04979 0.04319 -0.0435 0.0204 1.0000 13.000 1.2397 0.05372 0.04719 -0.0419 0.0189 1.0000 13.500 1.2515 0.05778 0.05142 -0.0398 0.0171 1.0000 14.000 1.2680 0.06151 0.05530 -0.0386 0.0159 1.0000 14.500 1.2799 0.06561 0.05947 -0.0372 0.0141 1.0000 15.000 1.2953 0.06983 0.06390 -0.0366 0.0130 1.0000 15.500 1.3071 0.07431 0.06854 -0.0358 0.0120 1.0000 16.000 1.3193 0.07845 0.07280 -0.0343 0.0114 1.0000 16.500 1.3262 0.08356 0.07825 -0.0326 0.0110 1.0000 17.000 1.3225 0.09089 0.08592 -0.0339 0.0100 1.0000 17.500 1.3176 0.09826 0.09365 -0.0343 0.0098 1.0000 18.000 1.3020 0.10757 0.10338 -0.0357 0.0096 1.0000 18.500 1.2942 0.11613 0.11214 -0.0387 0.0092 1.0000 19.000 1.2816 0.12563 0.12185 -0.0425 0.0089 1.0000 19.500 1.2413 0.14153 0.13824 -0.0505 0.0084 1.0000 20.000 1.2264 0.15267 0.14960 -0.0564 0.0088 1.0000 20.500 1.1771 0.17431 0.17177 -0.0704 0.0090 1.0000