XFOIL Version 6.94 Calculated polar for: HQ 3.5/13 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 0.4784 0.00811 0.00296 -0.1025 0.7230 0.7127 0.500 0.5342 0.00818 0.00293 -0.1023 0.7087 0.7279 1.000 0.5885 0.00817 0.00294 -0.1019 0.6927 0.7402 1.500 0.6433 0.00823 0.00298 -0.1016 0.6779 0.7533 2.000 0.6978 0.00833 0.00303 -0.1012 0.6613 0.7671 2.500 0.7505 0.00840 0.00310 -0.1004 0.6414 0.7812 3.000 0.8027 0.00848 0.00320 -0.0996 0.6199 0.7965 3.500 0.8533 0.00859 0.00334 -0.0985 0.5923 0.8136 4.000 0.9005 0.00880 0.00349 -0.0968 0.5562 0.8337 4.500 0.9431 0.00910 0.00374 -0.0941 0.5067 0.8611 5.000 0.9845 0.00957 0.00414 -0.0914 0.4391 0.9541 5.500 1.0176 0.01080 0.00482 -0.0879 0.3463 1.0000 6.000 1.0525 0.01178 0.00549 -0.0845 0.2968 1.0000 6.500 1.0881 0.01260 0.00614 -0.0812 0.2651 1.0000 7.000 1.1212 0.01334 0.00679 -0.0774 0.2420 1.0000 7.500 1.1566 0.01402 0.00745 -0.0741 0.2252 1.0000 8.000 1.1883 0.01488 0.00822 -0.0703 0.2006 1.0000 8.500 1.2202 0.01578 0.00906 -0.0668 0.1790 1.0000 9.000 1.2498 0.01684 0.01005 -0.0631 0.1523 1.0000 9.500 1.2664 0.01865 0.01158 -0.0580 0.1084 1.0000 10.000 1.2833 0.02063 0.01338 -0.0534 0.0751 1.0000 10.500 1.2946 0.02311 0.01566 -0.0486 0.0414 1.0000 11.500 1.3088 0.02931 0.02177 -0.0398 0.0033 1.0000 12.000 1.3264 0.03191 0.02453 -0.0371 0.0030 1.0000 12.500 1.3414 0.03486 0.02768 -0.0346 0.0029 1.0000 13.000 1.3528 0.03833 0.03135 -0.0323 0.0028 1.0000 13.500 1.3608 0.04236 0.03560 -0.0305 0.0027 1.0000 14.000 1.3653 0.04703 0.04051 -0.0292 0.0027 1.0000 14.500 1.3648 0.05263 0.04635 -0.0285 0.0027 1.0000 15.000 1.3594 0.05933 0.05330 -0.0287 0.0026 1.0000 15.500 1.3485 0.06733 0.06157 -0.0301 0.0026 1.0000 16.000 1.3332 0.07674 0.07126 -0.0327 0.0026 1.0000 16.500 1.3144 0.08749 0.08229 -0.0367 0.0027 1.0000 17.000 1.2913 0.09975 0.09484 -0.0420 0.0027 1.0000 17.500 1.2675 0.11277 0.10812 -0.0483 0.0027 1.0000 18.000 1.2469 0.12552 0.12111 -0.0548 0.0027 1.0000 18.500 1.2300 0.13765 0.13345 -0.0613 0.0027 1.0000 19.000 1.2175 0.14885 0.14483 -0.0676 0.0027 1.0000 19.500 1.2099 0.15900 0.15514 -0.0735 0.0028 1.0000 20.000 1.2063 0.16822 0.16449 -0.0790 0.0028 1.0000 20.500 1.2045 0.17703 0.17345 -0.0844 0.0028 1.0000 21.000 1.2043 0.18540 0.18195 -0.0896 0.0029 1.0000 21.500 1.2044 0.19374 0.19043 -0.0950 0.0029 1.0000 22.000 1.2028 0.20256 0.19941 -0.1008 0.0029 1.0000 22.500 1.1994 0.21201 0.20903 -0.1071 0.0030 1.0000 23.000 1.1940 0.22220 0.21939 -0.1139 0.0030 1.0000 23.500 1.1850 0.23367 0.23104 -0.1215 0.0031 1.0000 24.000 1.1748 0.24607 0.24362 -0.1294 0.0032 1.0000 26.000 0.9336 0.37049 0.36903 -0.1735 0.0090 1.0000 26.500 0.9397 0.37976 0.37832 -0.1768 0.0086 1.0000 27.000 0.9469 0.38754 0.38614 -0.1794 0.0083 1.0000 27.500 0.9504 0.39951 0.39811 -0.1832 0.0082 1.0000 28.000 0.9541 0.41252 0.41114 -0.1870 0.0077 1.0000 28.500 0.9586 0.42301 0.42165 -0.1903 0.0072 1.0000 29.000 0.9630 0.43319 0.43185 -0.1935 0.0069 1.0000 29.500 0.9670 0.44285 0.44153 -0.1966 0.0066 1.0000 30.000 0.9710 0.45151 0.45022 -0.1994 0.0064 1.0000 30.500 0.9743 0.46219 0.46092 -0.2023 0.0063 1.0000 31.000 0.9766 0.47572 0.47445 -0.2060 0.0059 1.0000 31.500 0.9794 0.48666 0.48542 -0.2090 0.0052 1.0000 32.000 0.9817 0.49677 0.49555 -0.2119 0.0050 1.0000 32.500 0.9836 0.50559 0.50440 -0.2147 0.0047 1.0000 33.000 0.9850 0.51756 0.51637 -0.2176 0.0045 1.0000 33.500 0.9866 0.52929 0.52812 -0.2206 0.0044 1.0000 34.000 0.9880 0.54073 0.53959 -0.2234 0.0042 1.0000 34.500 0.9887 0.55133 0.55021 -0.2261 0.0038 1.0000 35.000 0.9891 0.56144 0.56034 -0.2288 0.0036 1.0000 35.500 0.9890 0.57080 0.56973 -0.2316 0.0033 1.0000 36.000 0.9883 0.57958 0.57853 -0.2342 0.0032 1.0000 37.000 0.9867 0.60157 0.60056 -0.2394 0.0031 1.0000 37.500 0.9860 0.61247 0.61148 -0.2419 0.0030 1.0000 38.000 0.9848 0.62286 0.62189 -0.2443 0.0026 1.0000 38.500 0.9828 0.63222 0.63127 -0.2467 0.0025 1.0000 39.000 0.9805 0.64134 0.64041 -0.2492 0.0023 1.0000 39.500 0.9777 0.64973 0.64882 -0.2516 0.0021 1.0000 40.000 0.9746 0.65798 0.65710 -0.2539 0.0020 1.0000 42.000 0.9593 0.69140 0.69061 -0.2627 0.0020 1.0000 42.500 0.9552 0.69985 0.69909 -0.2649 0.0020 1.0000 43.000 0.9506 0.70756 0.70681 -0.2669 0.0019 1.0000 43.500 0.9459 0.71533 0.71461 -0.2689 0.0019 1.0000 44.000 0.9405 0.72179 0.72109 -0.2709 0.0019 1.0000 44.500 0.9352 0.72871 0.72803 -0.2727 0.0019 1.0000 45.000 0.9295 0.73498 0.73432 -0.2746 0.0019 1.0000 45.500 0.9235 0.74092 0.74029 -0.2764 0.0018 1.0000 46.000 0.9172 0.74634 0.74573 -0.2782 0.0018 1.0000 46.500 0.9107 0.75170 0.75111 -0.2799 0.0017 1.0000 47.000 0.9037 0.75630 0.75573 -0.2816 0.0016 1.0000 47.500 0.8966 0.76098 0.76044 -0.2832 0.0015 1.0000 48.000 0.8893 0.76522 0.76469 -0.2848 0.0014 1.0000 48.500 0.8815 0.76839 0.76788 -0.2863 0.0013 1.0000 49.000 0.8736 0.77153 0.77105 -0.2879 0.0013 1.0000 49.500 0.8653 0.77409 0.77362 -0.2894 0.0012 1.0000 50.000 0.8568 0.77618 0.77574 -0.2909 0.0011 1.0000 50.500 0.8479 0.77757 0.77715 -0.2923 0.0011 1.0000