XFOIL Version 6.94 Calculated polar for: HQ 2.5/12 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 0.3441 0.00760 0.00258 -0.0744 0.7413 0.7298 0.500 0.3993 0.00764 0.00256 -0.0740 0.7250 0.7480 1.000 0.4548 0.00767 0.00255 -0.0737 0.7092 0.7619 1.500 0.5095 0.00766 0.00257 -0.0733 0.6914 0.7764 2.000 0.5640 0.00770 0.00260 -0.0729 0.6717 0.7920 2.500 0.6179 0.00776 0.00269 -0.0724 0.6504 0.8092 3.500 0.7214 0.00790 0.00288 -0.0704 0.5924 0.8510 4.000 0.7685 0.00802 0.00302 -0.0684 0.5482 0.8842 4.500 0.8198 0.00881 0.00334 -0.0679 0.4223 1.0000 5.000 0.8622 0.00981 0.00388 -0.0660 0.3324 1.0000 5.500 0.9021 0.01095 0.00454 -0.0638 0.2516 1.0000 6.000 0.9473 0.01170 0.00512 -0.0622 0.2132 1.0000 6.500 0.9881 0.01268 0.00580 -0.0600 0.1589 1.0000 7.000 1.0284 0.01363 0.00655 -0.0577 0.1218 1.0000 7.500 1.0606 0.01501 0.00759 -0.0541 0.0684 1.0000 8.000 1.0746 0.01718 0.00934 -0.0477 0.0052 1.0000 8.500 1.1044 0.01824 0.01050 -0.0435 0.0037 1.0000 9.000 1.1334 0.01941 0.01180 -0.0395 0.0033 1.0000 9.500 1.1600 0.02076 0.01332 -0.0355 0.0031 1.0000 10.000 1.1832 0.02240 0.01515 -0.0313 0.0030 1.0000 10.500 1.2030 0.02437 0.01732 -0.0273 0.0030 1.0000 11.000 1.2178 0.02680 0.01995 -0.0232 0.0030 1.0000 11.500 1.2285 0.02967 0.02301 -0.0194 0.0029 1.0000 12.000 1.2325 0.03331 0.02687 -0.0159 0.0030 1.0000 12.500 1.2322 0.03766 0.03145 -0.0132 0.0030 1.0000 13.000 1.2294 0.04270 0.03671 -0.0114 0.0030 1.0000 13.500 1.2218 0.04877 0.04302 -0.0105 0.0031 1.0000 14.000 1.2121 0.05576 0.05025 -0.0108 0.0031 1.0000 14.500 1.2027 0.06344 0.05817 -0.0122 0.0032 1.0000 15.000 1.1913 0.07212 0.06711 -0.0146 0.0033 1.0000 15.500 1.1807 0.08137 0.07663 -0.0180 0.0034 1.0000 16.000 1.1675 0.09171 0.08725 -0.0223 0.0034 1.0000 16.500 1.1532 0.10285 0.09867 -0.0277 0.0035 1.0000 17.000 1.1372 0.11497 0.11107 -0.0341 0.0036 1.0000 17.500 1.1203 0.12775 0.12412 -0.0413 0.0037 1.0000 18.000 1.1032 0.14108 0.13771 -0.0492 0.0038 1.0000 18.500 1.0845 0.15512 0.15200 -0.0578 0.0039 1.0000 19.000 1.0671 0.16932 0.16641 -0.0667 0.0039 1.0000 19.500 1.0539 0.18268 0.17995 -0.0749 0.0041 1.0000 20.000 1.0411 0.19758 0.19504 -0.0841 0.0042 1.0000 22.000 0.8416 0.28973 0.28804 -0.1331 0.0110 1.0000 22.500 0.8501 0.29842 0.29676 -0.1368 0.0103 1.0000 23.000 0.8606 0.30568 0.30404 -0.1398 0.0099 1.0000 23.500 0.8676 0.31561 0.31399 -0.1437 0.0097 1.0000 24.000 0.8727 0.32773 0.32611 -0.1483 0.0089 1.0000 24.500 0.8803 0.33705 0.33545 -0.1520 0.0083 1.0000 25.000 0.8880 0.34587 0.34429 -0.1555 0.0079 1.0000 26.000 0.9023 0.36443 0.36289 -0.1622 0.0076 1.0000 26.500 0.9076 0.37593 0.37440 -0.1662 0.0074 1.0000 27.000 0.9139 0.38635 0.38485 -0.1698 0.0070 1.0000 27.500 0.9198 0.39614 0.39466 -0.1732 0.0067 1.0000 28.000 0.9254 0.40595 0.40449 -0.1766 0.0064 1.0000 28.500 0.9308 0.41561 0.41417 -0.1800 0.0061 1.0000 29.000 0.9357 0.42491 0.42350 -0.1832 0.0059 1.0000 29.500 0.9405 0.43409 0.43270 -0.1864 0.0058 1.0000 30.500 0.9485 0.45444 0.45309 -0.1927 0.0057 1.0000 31.000 0.9518 0.46543 0.46410 -0.1962 0.0057 1.0000 31.500 0.9555 0.47675 0.47544 -0.1995 0.0054 1.0000 32.000 0.9585 0.48722 0.48594 -0.2026 0.0049 1.0000 32.500 0.9612 0.49735 0.49609 -0.2056 0.0045 1.0000 33.000 0.9634 0.50712 0.50588 -0.2087 0.0043 1.0000 33.500 0.9651 0.51650 0.51528 -0.2117 0.0042 1.0000 34.500 0.9675 0.53748 0.53629 -0.2174 0.0040 1.0000 35.000 0.9687 0.54824 0.54708 -0.2205 0.0040 1.0000 35.500 0.9699 0.55935 0.55821 -0.2232 0.0037 1.0000 36.000 0.9702 0.56926 0.56815 -0.2260 0.0035 1.0000 36.500 0.9703 0.57927 0.57818 -0.2288 0.0032 1.0000 37.000 0.9697 0.58866 0.58759 -0.2315 0.0030 1.0000 37.500 0.9686 0.59751 0.59646 -0.2343 0.0027 1.0000 38.000 0.9674 0.60658 0.60556 -0.2370 0.0027 1.0000 39.500 0.9616 0.63489 0.63393 -0.2446 0.0026 1.0000 40.000 0.9597 0.64467 0.64373 -0.2471 0.0025 1.0000 40.500 0.9570 0.65334 0.65243 -0.2494 0.0025 1.0000 41.000 0.9544 0.66227 0.66138 -0.2518 0.0025 1.0000 41.500 0.9511 0.67052 0.66965 -0.2542 0.0024 1.0000 42.000 0.9476 0.67858 0.67773 -0.2565 0.0023 1.0000 42.500 0.9434 0.68597 0.68515 -0.2587 0.0023 1.0000 43.000 0.9393 0.69356 0.69276 -0.2609 0.0022 1.0000 43.500 0.9347 0.70054 0.69977 -0.2631 0.0021 1.0000 44.000 0.9297 0.70724 0.70649 -0.2652 0.0020 1.0000 44.500 0.9246 0.71383 0.71310 -0.2673 0.0019 1.0000 45.000 0.9190 0.71982 0.71912 -0.2694 0.0018 1.0000 45.500 0.9132 0.72563 0.72496 -0.2714 0.0017 1.0000 46.000 0.9070 0.73087 0.73022 -0.2734 0.0016 1.0000 46.500 0.9004 0.73560 0.73496 -0.2754 0.0015 1.0000 47.000 0.8930 0.74004 0.73943 -0.2773 0.0015 1.0000