XFOIL Version 6.96 Calculated polar for: HQ 1.5/12 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -15.250 -0.8258 0.09075 0.08786 -0.0307 1.0000 0.0065 -15.000 -0.8604 0.07921 0.07615 -0.0376 1.0000 0.0066 -14.750 -0.8885 0.06940 0.06618 -0.0438 1.0000 0.0065 -14.500 -0.9139 0.06066 0.05725 -0.0497 1.0000 0.0065 -14.250 -0.9283 0.05458 0.05101 -0.0536 1.0000 0.0065 -14.000 -0.9432 0.04901 0.04528 -0.0570 1.0000 0.0065 -13.750 -0.9536 0.04458 0.04068 -0.0592 1.0000 0.0066 -13.500 -0.9635 0.04061 0.03655 -0.0607 1.0000 0.0065 -13.250 -0.9651 0.03782 0.03360 -0.0614 1.0000 0.0067 -13.000 -0.9706 0.03491 0.03054 -0.0617 1.0000 0.0068 -12.750 -0.9762 0.03230 0.02782 -0.0613 1.0000 0.0070 -12.500 -0.9770 0.03034 0.02573 -0.0604 1.0000 0.0070 -12.250 -0.9748 0.02889 0.02419 -0.0589 1.0000 0.0072 -12.000 -0.9719 0.02771 0.02292 -0.0568 1.0000 0.0073 -11.750 -0.9683 0.02656 0.02167 -0.0542 1.0000 0.0075 -11.500 -0.9577 0.02559 0.02061 -0.0526 1.0000 0.0077 -11.250 -0.9460 0.02462 0.01955 -0.0510 1.0000 0.0079 -11.000 -0.9332 0.02369 0.01850 -0.0493 1.0000 0.0082 -10.750 -0.9197 0.02279 0.01749 -0.0477 1.0000 0.0085 -10.500 -0.9060 0.02190 0.01649 -0.0460 1.0000 0.0088 -10.250 -0.8908 0.02117 0.01566 -0.0443 1.0000 0.0091 -9.750 -0.8450 0.01930 0.01362 -0.0444 0.9908 0.0100 -9.500 -0.8140 0.01858 0.01284 -0.0459 0.9850 0.0106 -9.250 -0.7835 0.01788 0.01205 -0.0471 0.9779 0.0112 -9.000 -0.7519 0.01715 0.01123 -0.0486 0.9708 0.0119 -8.750 -0.7217 0.01648 0.01046 -0.0496 0.9613 0.0124 -8.500 -0.6908 0.01590 0.00978 -0.0507 0.9514 0.0129 -8.250 -0.6631 0.01507 0.00889 -0.0514 0.9391 0.0139 -8.000 -0.6354 0.01456 0.00831 -0.0517 0.9261 0.0149 -7.750 -0.6094 0.01411 0.00778 -0.0516 0.9136 0.0158 -7.500 -0.5845 0.01370 0.00726 -0.0512 0.9021 0.0166 -7.250 -0.5599 0.01330 0.00677 -0.0507 0.8915 0.0175 -7.000 -0.5359 0.01285 0.00626 -0.0501 0.8815 0.0192 -6.750 -0.5110 0.01251 0.00587 -0.0497 0.8720 0.0211 -6.500 -0.4856 0.01222 0.00548 -0.0493 0.8635 0.0229 -6.250 -0.4608 0.01185 0.00508 -0.0488 0.8552 0.0263 -6.000 -0.4350 0.01157 0.00476 -0.0485 0.8473 0.0300 -5.750 -0.4096 0.01126 0.00444 -0.0481 0.8399 0.0362 -5.500 -0.3837 0.01098 0.00414 -0.0478 0.8322 0.0436 -5.250 -0.3577 0.01074 0.00387 -0.0476 0.8251 0.0523 -5.000 -0.3314 0.01048 0.00362 -0.0473 0.8178 0.0625 -4.750 -0.3053 0.01022 0.00338 -0.0471 0.8108 0.0764 -4.500 -0.2791 0.00994 0.00315 -0.0469 0.8038 0.0952 -4.250 -0.2529 0.00967 0.00294 -0.0467 0.7969 0.1183 -4.000 -0.2267 0.00937 0.00274 -0.0465 0.7901 0.1486 -3.750 -0.2006 0.00907 0.00255 -0.0463 0.7832 0.1861 -3.500 -0.1740 0.00883 0.00238 -0.0461 0.7767 0.2177 -3.250 -0.1476 0.00856 0.00221 -0.0460 0.7697 0.2542 -3.000 -0.1215 0.00824 0.00203 -0.0458 0.7631 0.3035 -2.750 -0.0961 0.00782 0.00187 -0.0456 0.7559 0.3815 -2.500 -0.0703 0.00751 0.00176 -0.0453 0.7493 0.4484 -2.250 -0.0437 0.00731 0.00170 -0.0451 0.7419 0.4997 -2.000 -0.0166 0.00722 0.00165 -0.0449 0.7352 0.5314 -1.750 0.0111 0.00715 0.00161 -0.0448 0.7273 0.5548 -1.500 0.0386 0.00712 0.00158 -0.0446 0.7187 0.5746 -1.250 0.0660 0.00709 0.00156 -0.0444 0.7083 0.5946 -1.000 0.0937 0.00708 0.00154 -0.0443 0.6992 0.6114 -0.750 0.1214 0.00709 0.00153 -0.0442 0.6906 0.6241 -0.500 0.1492 0.00708 0.00153 -0.0441 0.6812 0.6378 -0.250 0.1769 0.00709 0.00153 -0.0439 0.6726 0.6502 0.000 0.2047 0.00713 0.00153 -0.0438 0.6632 0.6613 0.250 0.2324 0.00713 0.00155 -0.0437 0.6526 0.6708 0.500 0.2601 0.00716 0.00156 -0.0436 0.6414 0.6797 0.750 0.2877 0.00720 0.00158 -0.0435 0.6306 0.6890 1.000 0.3153 0.00724 0.00161 -0.0434 0.6196 0.6963 1.250 0.3430 0.00728 0.00164 -0.0433 0.6072 0.7030 1.500 0.3706 0.00733 0.00168 -0.0432 0.5953 0.7093 1.750 0.3981 0.00739 0.00172 -0.0430 0.5823 0.7161 2.000 0.4253 0.00747 0.00177 -0.0429 0.5660 0.7228 2.250 0.4521 0.00756 0.00184 -0.0426 0.5474 0.7298 2.500 0.4788 0.00768 0.00191 -0.0424 0.5278 0.7371 2.750 0.5049 0.00782 0.00201 -0.0420 0.5026 0.7443 3.000 0.5307 0.00802 0.00212 -0.0416 0.4741 0.7519 3.250 0.5557 0.00825 0.00226 -0.0411 0.4417 0.7593 3.500 0.5804 0.00854 0.00243 -0.0406 0.4037 0.7672 3.750 0.6042 0.00889 0.00263 -0.0400 0.3607 0.7753 4.000 0.6276 0.00929 0.00285 -0.0393 0.3152 0.7836 4.250 0.6506 0.00971 0.00311 -0.0386 0.2764 0.7927 4.500 0.6745 0.01004 0.00336 -0.0380 0.2500 0.8018 4.750 0.6995 0.01027 0.00356 -0.0375 0.2344 0.8118 5.000 0.7245 0.01047 0.00377 -0.0371 0.2227 0.8229 5.250 0.7494 0.01064 0.00398 -0.0366 0.2107 0.8346 5.500 0.7740 0.01083 0.00420 -0.0360 0.1985 0.8481 5.750 0.7978 0.01102 0.00442 -0.0353 0.1846 0.8645 6.000 0.8204 0.01126 0.00467 -0.0343 0.1659 0.8881 6.250 0.8469 0.01157 0.00498 -0.0343 0.1408 0.9304 6.500 0.8828 0.01208 0.00538 -0.0365 0.1135 1.0000 6.750 0.9049 0.01257 0.00577 -0.0358 0.0934 1.0000 7.000 0.9267 0.01307 0.00617 -0.0350 0.0763 1.0000 7.250 0.9488 0.01353 0.00658 -0.0342 0.0646 1.0000 7.500 0.9711 0.01397 0.00699 -0.0334 0.0567 1.0000 7.750 0.9927 0.01446 0.00743 -0.0326 0.0486 1.0000 8.000 1.0151 0.01485 0.00783 -0.0319 0.0442 1.0000 8.250 1.0365 0.01531 0.00827 -0.0310 0.0398 1.0000 8.500 1.0580 0.01574 0.00873 -0.0301 0.0369 1.0000 8.750 1.0798 0.01613 0.00917 -0.0293 0.0351 1.0000 9.000 1.1006 0.01657 0.00963 -0.0284 0.0329 1.0000 9.250 1.1203 0.01708 0.01014 -0.0273 0.0303 1.0000 9.500 1.1397 0.01758 0.01067 -0.0262 0.0285 1.0000 9.750 1.1595 0.01801 0.01116 -0.0251 0.0270 1.0000 10.000 1.1780 0.01848 0.01168 -0.0238 0.0250 1.0000 10.250 1.1936 0.01901 0.01222 -0.0221 0.0226 1.0000 10.500 1.2087 0.01956 0.01279 -0.0203 0.0206 1.0000 10.750 1.2235 0.02012 0.01339 -0.0186 0.0187 1.0000 11.000 1.2368 0.02079 0.01406 -0.0168 0.0164 1.0000 11.250 1.2502 0.02147 0.01479 -0.0150 0.0146 1.0000 11.500 1.2620 0.02227 0.01562 -0.0132 0.0123 1.0000 11.750 1.2716 0.02325 0.01661 -0.0113 0.0083 1.0000 12.000 1.2792 0.02440 0.01780 -0.0093 0.0060 1.0000 12.250 1.2870 0.02559 0.01905 -0.0075 0.0053 1.0000 12.500 1.2956 0.02676 0.02029 -0.0060 0.0050 1.0000 12.750 1.3022 0.02814 0.02176 -0.0044 0.0046 1.0000 13.000 1.3089 0.02956 0.02327 -0.0030 0.0043 1.0000 13.250 1.3155 0.03104 0.02486 -0.0018 0.0041 1.0000 13.500 1.3220 0.03259 0.02650 -0.0007 0.0041 1.0000 13.750 1.3264 0.03438 0.02841 0.0003 0.0039 1.0000 14.000 1.3295 0.03636 0.03051 0.0011 0.0038 1.0000 14.250 1.3323 0.03845 0.03272 0.0018 0.0037 1.0000 14.500 1.3338 0.04075 0.03514 0.0023 0.0036 1.0000 14.750 1.3324 0.04346 0.03798 0.0025 0.0034 1.0000 15.000 1.3322 0.04614 0.04079 0.0026 0.0034 1.0000 15.250 1.3288 0.04931 0.04408 0.0023 0.0033 1.0000 15.500 1.3239 0.05283 0.04773 0.0017 0.0033 1.0000 15.750 1.3153 0.05703 0.05208 0.0007 0.0032 1.0000 16.000 1.3056 0.06166 0.05686 -0.0008 0.0031 1.0000 16.250 1.2989 0.06610 0.06143 -0.0025 0.0032 1.0000 16.500 1.2855 0.07184 0.06734 -0.0050 0.0031 1.0000 16.750 1.2693 0.07842 0.07407 -0.0082 0.0031 1.0000 17.000 1.2572 0.08452 0.08032 -0.0113 0.0031 1.0000 17.250 1.2408 0.09172 0.08768 -0.0150 0.0031 1.0000 17.500 1.2165 0.10076 0.09690 -0.0200 0.0030 1.0000 17.750 1.1999 0.10844 0.10472 -0.0241 0.0031 1.0000 18.000 1.1832 0.11631 0.11272 -0.0285 0.0031 1.0000 18.250 1.1622 0.12520 0.12176 -0.0335 0.0031 1.0000 18.500 1.1399 0.13461 0.13131 -0.0389 0.0032 1.0000