XFOIL Version 6.94 Calculated polar for: HQ 2.1/9.5 AIRFOIL 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 0.3079 0.00674 0.00227 -0.0690 0.8046 0.7827 0.500 0.3628 0.00674 0.00227 -0.0684 0.7913 0.8042 1.000 0.4171 0.00672 0.00228 -0.0677 0.7761 0.8261 1.500 0.4707 0.00670 0.00231 -0.0669 0.7584 0.8509 2.000 0.5228 0.00666 0.00233 -0.0657 0.7370 0.8783 2.500 0.5720 0.00659 0.00230 -0.0636 0.7042 0.9168 3.000 0.6351 0.00662 0.00220 -0.0648 0.6231 1.0000 3.500 0.6808 0.00752 0.00246 -0.0631 0.4893 1.0000 4.000 0.7288 0.00839 0.00292 -0.0619 0.4022 1.0000 4.500 0.7742 0.00949 0.00343 -0.0605 0.2865 1.0000 5.000 0.8208 0.01054 0.00398 -0.0593 0.1891 1.0000 5.500 0.8634 0.01203 0.00485 -0.0576 0.0866 1.0000 6.000 0.9107 0.01300 0.00559 -0.0565 0.0517 1.0000 6.500 0.9583 0.01390 0.00638 -0.0553 0.0295 1.0000 7.000 1.0053 0.01480 0.00725 -0.0540 0.0208 1.0000 7.500 1.0512 0.01575 0.00820 -0.0526 0.0148 1.0000 8.000 1.0970 0.01664 0.00915 -0.0512 0.0122 1.0000 8.500 1.1420 0.01752 0.01013 -0.0497 0.0102 1.0000 9.000 1.1839 0.01861 0.01127 -0.0477 0.0034 1.0000 9.500 1.2215 0.02000 0.01277 -0.0451 0.0023 1.0000 10.000 1.2570 0.02141 0.01435 -0.0423 0.0021 1.0000 10.500 1.2867 0.02293 0.01608 -0.0385 0.0020 1.0000 11.000 1.3092 0.02460 0.01797 -0.0338 0.0020 1.0000 11.500 1.3277 0.02658 0.02021 -0.0290 0.0019 1.0000 12.000 1.3425 0.02894 0.02285 -0.0246 0.0019 1.0000 12.500 1.3531 0.03179 0.02599 -0.0204 0.0019 1.0000 13.000 1.3578 0.03537 0.02988 -0.0168 0.0019 1.0000 13.500 1.3573 0.03976 0.03459 -0.0140 0.0019 1.0000 14.000 1.3498 0.04535 0.04052 -0.0125 0.0019 1.0000 14.500 1.3352 0.05253 0.04803 -0.0127 0.0019 1.0000 15.000 1.3122 0.06212 0.05798 -0.0156 0.0019 1.0000 15.500 1.2814 0.07510 0.07132 -0.0222 0.0020 1.0000 16.000 1.2410 0.09218 0.08877 -0.0323 0.0020 1.0000 16.500 1.1911 0.11282 0.10974 -0.0447 0.0020 1.0000 17.000 1.1260 0.13912 0.13636 -0.0602 0.0020 1.0000 17.500 1.0517 0.17046 0.16793 -0.0781 0.0021 1.0000 18.000 1.0224 0.19065 0.18820 -0.0895 0.0022 1.0000 18.500 1.0172 0.20387 0.20148 -0.0970 0.0023 1.0000 19.000 1.0180 0.21535 0.21302 -0.1035 0.0023 1.0000