XFOIL Version 6.96 Calculated polar for: HQ-2.0/9 9.0% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.4714 0.08829 0.08475 -0.0276 1.0000 0.0123 -9.000 -0.4765 0.08284 0.07935 -0.0305 1.0000 0.0119 -8.750 -0.4861 0.07628 0.07287 -0.0343 1.0000 0.0115 -8.500 -0.5024 0.06737 0.06409 -0.0409 1.0000 0.0108 -8.250 -0.5120 0.06063 0.05731 -0.0465 1.0000 0.0106 -8.000 -0.5203 0.05539 0.05196 -0.0488 1.0000 0.0105 -7.750 -0.5275 0.05036 0.04680 -0.0495 1.0000 0.0104 -7.500 -0.5330 0.04536 0.04159 -0.0492 1.0000 0.0103 -7.250 -0.5367 0.04046 0.03640 -0.0480 1.0000 0.0103 -7.000 -0.5312 0.03521 0.03069 -0.0478 0.9983 0.0103 -6.750 -0.5060 0.02942 0.02416 -0.0507 0.9922 0.0103 -6.500 -0.4769 0.02532 0.01937 -0.0527 0.9873 0.0106 -6.250 -0.4485 0.02213 0.01566 -0.0540 0.9823 0.0111 -6.000 -0.4164 0.02050 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4.250 0.7201 0.01093 0.00389 -0.0536 0.4058 1.0000 4.500 0.7427 0.01148 0.00422 -0.0529 0.3534 1.0000 4.750 0.7654 0.01204 0.00459 -0.0522 0.3068 1.0000 5.000 0.7879 0.01264 0.00499 -0.0515 0.2632 1.0000 5.250 0.8111 0.01318 0.00544 -0.0510 0.2274 1.0000 5.500 0.8344 0.01372 0.00588 -0.0504 0.1945 1.0000 5.750 0.8575 0.01429 0.00635 -0.0498 0.1637 1.0000 6.000 0.8801 0.01493 0.00687 -0.0492 0.1301 1.0000 6.250 0.9018 0.01567 0.00747 -0.0485 0.0979 1.0000 6.500 0.9240 0.01638 0.00812 -0.0478 0.0779 1.0000 6.750 0.9460 0.01710 0.00888 -0.0470 0.0653 1.0000 7.000 0.9677 0.01783 0.00960 -0.0463 0.0532 1.0000 7.250 0.9896 0.01850 0.01027 -0.0456 0.0419 1.0000 7.500 1.0106 0.01930 0.01110 -0.0448 0.0349 1.0000 7.750 1.0321 0.02001 0.01190 -0.0440 0.0277 1.0000 8.000 1.0520 0.02091 0.01286 -0.0429 0.0205 1.0000 8.250 1.0699 0.02206 0.01404 -0.0417 0.0163 1.0000 8.500 1.0879 0.02315 0.01533 -0.0404 0.0141 1.0000 8.750 1.1050 0.02430 0.01660 -0.0390 0.0126 1.0000 9.000 1.1194 0.02571 0.01810 -0.0374 0.0114 1.0000 9.250 1.1343 0.02705 0.01960 -0.0359 0.0104 1.0000 9.500 1.1490 0.02836 0.02109 -0.0343 0.0094 1.0000 9.750 1.1615 0.02992 0.02284 -0.0326 0.0089 1.0000 10.000 1.1721 0.03158 0.02468 -0.0306 0.0084 1.0000 10.250 1.1801 0.03329 0.02657 -0.0284 0.0081 1.0000 10.500 1.1860 0.03510 0.02857 -0.0261 0.0077 1.0000 10.750 1.1897 0.03713 0.03081 -0.0238 0.0075 1.0000 11.000 1.1909 0.03937 0.03326 -0.0217 0.0073 1.0000 11.250 1.1886 0.04204 0.03616 -0.0196 0.0071 1.0000 11.500 1.1845 0.04498 0.03940 -0.0179 0.0070 1.0000 11.750 1.1776 0.04827 0.04294 -0.0166 0.0070 1.0000 12.000 1.1661 0.05225 0.04718 -0.0159 0.0069 1.0000 12.250 1.1533 0.05664 0.05182 -0.0159 0.0068 1.0000 12.500 1.1406 0.06127 0.05669 -0.0168 0.0068 1.0000 12.750 1.1262 0.06654 0.06219 -0.0186 0.0068 1.0000 13.000 1.1085 0.07289 0.06876 -0.0215 0.0068 1.0000 13.250 1.0925 0.07958 0.07566 -0.0253 0.0068 1.0000 13.500 1.0757 0.08723 0.08350 -0.0302 0.0068 1.0000 13.750 1.0585 0.09579 0.09224 -0.0358 0.0069 1.0000 14.000 1.0382 0.10593 0.10252 -0.0424 0.0070 1.0000 14.250 1.0055 0.12081 0.11761 -0.0517 0.0073 1.0000