XFOIL Version 6.94 Calculated polar for: AH21 7% version (Andrew Hollom) 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 0.2622 0.00794 0.00431 -0.0690 0.9099 0.9492 0.500 0.3563 0.00744 0.00383 -0.0764 0.9056 0.9768 1.000 0.4534 0.00689 0.00327 -0.0845 0.8974 0.9866 1.500 0.5358 0.00661 0.00301 -0.0901 0.8778 0.9982 2.000 0.6025 0.00628 0.00262 -0.0920 0.8424 1.0000 2.500 0.6603 0.00623 0.00238 -0.0921 0.7845 1.0000 3.000 0.6938 0.00669 0.00237 -0.0870 0.6708 1.0000 3.500 0.7133 0.00773 0.00266 -0.0793 0.5149 1.0000 4.000 0.7385 0.00918 0.00322 -0.0735 0.3334 1.0000 4.500 0.7757 0.01046 0.00398 -0.0703 0.2021 1.0000 5.000 0.8187 0.01144 0.00459 -0.0682 0.1307 1.0000 5.500 0.8622 0.01245 0.00529 -0.0662 0.0800 1.0000 6.000 0.9075 0.01329 0.00595 -0.0645 0.0535 1.0000 6.500 0.9521 0.01421 0.00672 -0.0627 0.0365 1.0000 7.000 0.9985 0.01489 0.00749 -0.0612 0.0330 1.0000 7.500 1.0426 0.01579 0.00843 -0.0592 0.0284 1.0000 8.000 1.0805 0.01736 0.01046 -0.0559 0.0285 1.0000 8.500 1.1198 0.01870 0.01198 -0.0532 0.0266 1.0000 9.000 1.1511 0.02108 0.01458 -0.0493 0.0206 1.0000 9.500 1.1940 0.02128 0.01483 -0.0474 0.0175 1.0000 10.000 1.2286 0.02261 0.01627 -0.0441 0.0138 1.0000 10.500 1.2569 0.02447 0.01827 -0.0402 0.0114 1.0000 11.000 1.2659 0.02875 0.02302 -0.0339 0.0093 1.0000 11.500 1.3074 0.02831 0.02250 -0.0322 0.0084 1.0000 12.000 1.3338 0.02983 0.02418 -0.0287 0.0060 1.0000 12.500 1.3334 0.03404 0.02884 -0.0225 0.0053 1.0000 13.000 1.3196 0.03954 0.03486 -0.0165 0.0051 1.0000 13.500 1.2946 0.04659 0.04245 -0.0121 0.0051 1.0000 14.000 1.2510 0.05650 0.05290 -0.0109 0.0051 1.0000 14.500 1.2069 0.06937 0.06623 -0.0154 0.0051 1.0000 15.000 1.1578 0.08739 0.08466 -0.0268 0.0052 1.0000 15.500 1.1025 0.11053 0.10811 -0.0420 0.0054 1.0000 16.000 0.9288 0.16645 0.16416 -0.0733 0.0082 1.0000 16.500 0.9112 0.18511 0.18278 -0.0815 0.0074 1.0000 17.000 0.9023 0.20295 0.20058 -0.0883 0.0073 1.0000 17.500 0.9029 0.21715 0.21477 -0.0936 0.0079 1.0000 18.500 0.9181 0.24066 0.23831 -0.1012 0.0106 1.0000 19.000 0.9242 0.25264 0.25030 -0.1054 0.0107 1.0000 19.500 0.9314 0.26369 0.26137 -0.1090 0.0104 1.0000 20.000 0.9357 0.27567 0.27337 -0.1124 0.0099 1.0000