XFOIL Version 6.96 Calculated polar for: HQ 1.0/12 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.5667 0.09457 0.08777 -0.0249 1.0000 0.1851 -9.500 -0.5489 0.08958 0.08272 -0.0242 1.0000 0.1789 -9.250 -0.6569 0.07382 0.06710 -0.0396 1.0000 0.1411 -9.000 -0.6606 0.06891 0.06216 -0.0398 1.0000 0.1393 -8.750 -0.6721 0.06392 0.05706 -0.0398 1.0000 0.1370 -8.500 -0.6858 0.05890 0.05181 -0.0393 1.0000 0.1344 -8.250 -0.6966 0.05408 0.04662 -0.0381 1.0000 0.1325 -8.000 -0.6960 0.05042 0.04267 -0.0365 1.0000 0.1351 -7.750 -0.6958 0.04688 0.03868 -0.0345 1.0000 0.1385 -7.500 -0.6941 0.04347 0.03464 -0.0321 1.0000 0.1413 -7.250 -0.6787 0.04079 0.03205 -0.0306 1.0000 0.1485 -7.000 -0.6712 0.03821 0.02887 -0.0281 1.0000 0.1556 -6.750 -0.6546 0.03584 0.02654 -0.0265 1.0000 0.1640 -6.500 -0.6410 0.03381 0.02427 -0.0245 1.0000 0.1748 -6.250 -0.6258 0.03186 0.02193 -0.0225 1.0000 0.1853 -6.000 -0.6093 0.03023 0.02019 -0.0207 1.0000 0.1995 -5.750 -0.5916 0.02861 0.01864 -0.0189 1.0000 0.2162 -5.500 -0.5733 0.02708 0.01720 -0.0172 1.0000 0.2360 -5.250 -0.5567 0.02564 0.01590 -0.0153 1.0000 0.2654 -5.000 -0.5407 0.02411 0.01463 -0.0131 1.0000 0.3065 -4.750 -0.5286 0.02261 0.01373 -0.0104 1.0000 0.3765 -4.500 -0.5206 0.02166 0.01374 -0.0058 1.0000 0.4861 -4.250 -0.5146 0.02206 0.01462 0.0004 1.0000 0.5863 -4.000 -0.5080 0.02289 0.01555 0.0069 1.0000 0.6524 -3.750 -0.5011 0.02358 0.01620 0.0130 1.0000 0.7034 -3.500 -0.4936 0.02420 0.01675 0.0193 1.0000 0.7460 -3.250 -0.4841 0.02469 0.01717 0.0253 1.0000 0.7851 -3.000 -0.4716 0.02500 0.01736 0.0304 1.0000 0.8249 -2.750 -0.4448 0.02543 0.01761 0.0331 1.0000 0.8665 -2.500 -0.3559 0.02648 0.01819 0.0251 1.0000 0.9081 -2.250 -0.2460 0.02683 0.01802 0.0107 1.0000 0.9391 -2.000 -0.1510 0.02654 0.01739 -0.0025 1.0000 0.9662 -1.750 -0.0460 0.02581 0.01633 -0.0183 1.0000 0.9956 -1.500 -0.0357 0.02559 0.01605 -0.0183 1.0000 1.0000 -1.250 -0.0439 0.02548 0.01592 -0.0150 1.0000 1.0000 -1.000 -0.0520 0.02533 0.01575 -0.0116 1.0000 1.0000 -0.750 -0.0604 0.02514 0.01552 -0.0083 1.0000 1.0000 -0.500 -0.0693 0.02490 0.01526 -0.0048 1.0000 1.0000 -0.250 -0.0789 0.02460 0.01493 -0.0012 1.0000 1.0000 0.000 -0.0892 0.02423 0.01454 0.0025 1.0000 1.0000 0.250 -0.0976 0.02387 0.01413 0.0060 1.0000 1.0000 0.500 -0.0991 0.02367 0.01385 0.0086 1.0000 1.0000 0.750 -0.0913 0.02375 0.01383 0.0097 1.0000 1.0000 1.000 -0.0782 0.02404 0.01402 0.0102 1.0000 1.0000 1.250 -0.0352 0.02509 0.01499 0.0051 0.9886 1.0000 1.500 0.0089 0.02621 0.01605 0.0001 0.9755 1.0000 1.750 0.0516 0.02730 0.01710 -0.0045 0.9613 1.0000 2.000 0.0977 0.02840 0.01819 -0.0094 0.9444 1.0000 2.250 0.1510 0.02950 0.01931 -0.0151 0.9234 1.0000 2.500 0.1981 0.03031 0.02017 -0.0193 0.9006 1.0000 2.750 0.2497 0.03112 0.02106 -0.0239 0.8801 1.0000 3.000 0.2845 0.03176 0.02178 -0.0257 0.8591 1.0000 3.250 0.3350 0.03232 0.02247 -0.0295 0.8385 1.0000 3.500 0.3712 0.03283 0.02308 -0.0310 0.8166 1.0000 3.750 0.4241 0.03297 0.02344 -0.0343 0.7942 1.0000 4.000 0.4641 0.03311 0.02374 -0.0356 0.7699 1.0000 4.250 0.5275 0.03232 0.02323 -0.0386 0.7476 1.0000 4.500 0.5610 0.03202 0.02309 -0.0377 0.7206 1.0000 4.750 0.5994 0.03127 0.02253 -0.0367 0.6930 1.0000 5.000 0.6386 0.03019 0.02164 -0.0353 0.6643 1.0000 5.250 0.6763 0.02891 0.02049 -0.0333 0.6334 1.0000 5.500 0.7127 0.02757 0.01923 -0.0311 0.6007 1.0000 5.750 0.7395 0.02691 0.01858 -0.0285 0.5641 1.0000 6.000 0.7691 0.02617 0.01772 -0.0261 0.5268 1.0000 6.250 0.7913 0.02617 0.01762 -0.0236 0.4871 1.0000 6.500 0.8138 0.02640 0.01769 -0.0214 0.4473 1.0000 6.750 0.8360 0.02696 0.01798 -0.0193 0.4074 1.0000 7.000 0.8544 0.02799 0.01886 -0.0173 0.3681 1.0000 7.250 0.8741 0.02926 0.01992 -0.0155 0.3313 1.0000 7.500 0.8933 0.03081 0.02135 -0.0139 0.2980 1.0000 7.750 0.9131 0.03259 0.02307 -0.0126 0.2691 1.0000 8.000 0.9344 0.03453 0.02489 -0.0115 0.2446 1.0000 8.250 0.9509 0.03656 0.02709 -0.0099 0.2241 1.0000 8.500 0.9694 0.03863 0.02924 -0.0086 0.2067 1.0000 8.750 0.9861 0.04093 0.03170 -0.0073 0.1921 1.0000 9.000 0.9998 0.04327 0.03426 -0.0056 0.1788 1.0000 9.250 1.0107 0.04618 0.03749 -0.0039 0.1690 1.0000 9.500 1.0247 0.04863 0.04002 -0.0026 0.1580 1.0000 9.750 1.0250 0.05201 0.04387 -0.0002 0.1513 1.0000 10.000 1.0323 0.05517 0.04717 0.0013 0.1437 1.0000 10.250 1.0190 0.05921 0.05166 0.0039 0.1405 1.0000 10.500 1.0068 0.06321 0.05596 0.0060 0.1376 1.0000 10.750 0.9986 0.06716 0.06008 0.0076 0.1352 1.0000 11.000 0.9826 0.07132 0.06438 0.0093 0.1341 1.0000 11.250 0.9657 0.07588 0.06904 0.0102 0.1332 1.0000 11.500 0.9490 0.08107 0.07431 0.0101 0.1325 1.0000