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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -12.000 -0.6643 0.08042 0.07674 -0.0363 1.0000 0.0290 -11.750 -0.6919 0.07136 0.06763 -0.0428 1.0000 0.0283 -11.500 -0.7168 0.06439 0.06054 -0.0477 1.0000 0.0278 -11.250 -0.7439 0.05835 0.05433 -0.0510 1.0000 0.0276 -11.000 -0.7660 0.05378 0.04958 -0.0522 1.0000 0.0272 -10.750 -0.7892 0.04985 0.04544 -0.0516 1.0000 0.0272 -10.500 -0.8088 0.04662 0.04199 -0.0490 1.0000 0.0271 -10.250 -0.8206 0.04320 0.03827 -0.0466 1.0000 0.0272 -10.000 -0.8248 0.04021 0.03493 -0.0443 1.0000 0.0280 -9.750 -0.8234 0.03764 0.03197 -0.0421 1.0000 0.0288 -9.500 -0.8173 0.03567 0.02961 -0.0398 1.0000 0.0295 -9.250 -0.8128 0.03169 0.02523 -0.0377 1.0000 0.0303 -9.000 -0.7996 0.02937 0.02278 -0.0363 1.0000 0.0314 -8.750 -0.7843 0.02796 0.02127 -0.0347 1.0000 0.0330 -8.500 -0.7690 0.02656 0.01971 -0.0330 1.0000 0.0349 -8.250 -0.7534 0.02564 0.01857 -0.0310 1.0000 0.0376 -8.000 -0.7400 0.02372 0.01657 -0.0291 1.0000 0.0405 -7.750 -0.7264 0.02290 0.01574 -0.0270 1.0000 0.0437 -7.500 -0.7143 0.02209 0.01477 -0.0244 1.0000 0.0471 -7.250 -0.7051 0.02090 0.01355 -0.0216 1.0000 0.0513 -7.000 -0.6950 0.02041 0.01305 -0.0190 1.0000 0.0560 -6.750 -0.6831 0.01990 0.01239 -0.0165 1.0000 0.0606 -6.500 -0.6495 0.01883 0.01138 -0.0185 0.9958 0.0694 -6.250 -0.6132 0.01787 0.01040 -0.0209 0.9905 0.0783 -6.000 -0.5758 0.01708 0.00957 -0.0233 0.9851 0.0887 -5.750 -0.5385 0.01644 0.00889 -0.0257 0.9798 0.0998 -5.500 -0.5040 0.01555 0.00808 -0.0277 0.9735 0.1150 -5.250 -0.4656 0.01465 0.00731 -0.0304 0.9694 0.1410 -5.000 -0.4356 0.01372 0.00672 -0.0316 0.9614 0.1924 -4.750 -0.3995 0.01274 0.00616 -0.0342 0.9569 0.2813 -4.500 -0.3702 0.01190 0.00581 -0.0352 0.9497 0.3851 -4.250 -0.3384 0.01137 0.00567 -0.0362 0.9435 0.4875 -4.000 -0.3062 0.01119 0.00566 -0.0369 0.9373 0.5529 -3.750 -0.2753 0.01116 0.00567 -0.0372 0.9300 0.5933 -3.500 -0.2419 0.01116 0.00565 -0.0380 0.9246 0.6241 -3.250 -0.2145 0.01121 0.00569 -0.0375 0.9160 0.6475 -3.000 -0.1831 0.01126 0.00570 -0.0378 0.9105 0.6697 -2.750 -0.1579 0.01135 0.00576 -0.0369 0.9014 0.6885 -2.500 -0.1292 0.01142 0.00582 -0.0364 0.8953 0.7054 -2.250 -0.1045 0.01152 0.00591 -0.0354 0.8863 0.7209 -2.000 -0.0773 0.01156 0.00589 -0.0348 0.8796 0.7341 -1.750 -0.0517 0.01159 0.00591 -0.0340 0.8710 0.7450 -1.500 -0.0251 0.01160 0.00590 -0.0334 0.8640 0.7548 -1.250 0.0005 0.01161 0.00588 -0.0327 0.8557 0.7653 -1.000 0.0264 0.01165 0.00588 -0.0319 0.8487 0.7773 -0.750 0.0515 0.01168 0.00593 -0.0309 0.8408 0.7879 -0.500 0.0768 0.01171 0.00595 -0.0300 0.8335 0.7991 -0.250 0.1017 0.01169 0.00592 -0.0290 0.8248 0.8105 0.000 0.1264 0.01166 0.00588 -0.0280 0.8151 0.8212 0.250 0.1525 0.01156 0.00575 -0.0271 0.8067 0.8290 0.500 0.1774 0.01149 0.00568 -0.0263 0.7960 0.8383 0.750 0.2028 0.01142 0.00562 -0.0254 0.7866 0.8468 1.000 0.2289 0.01132 0.00549 -0.0246 0.7777 0.8556 1.250 0.2537 0.01125 0.00544 -0.0238 0.7668 0.8658 1.500 0.2793 0.01118 0.00540 -0.0230 0.7579 0.8747 1.750 0.3052 0.01111 0.00533 -0.0222 0.7490 0.8848 2.000 0.3303 0.01106 0.00532 -0.0215 0.7386 0.8961 2.250 0.3572 0.01099 0.00527 -0.0209 0.7292 0.9061 2.500 0.3852 0.01092 0.00522 -0.0205 0.7187 0.9167 2.750 0.4142 0.01088 0.00522 -0.0205 0.7066 0.9282 3.000 0.4451 0.01084 0.00522 -0.0209 0.6940 0.9403 3.250 0.4814 0.01079 0.00519 -0.0223 0.6794 0.9499 3.500 0.5189 0.01074 0.00516 -0.0241 0.6626 0.9596 3.750 0.5568 0.01070 0.00509 -0.0260 0.6434 0.9699 4.000 0.5983 0.01066 0.00509 -0.0288 0.6178 0.9781 4.250 0.6393 0.01066 0.00506 -0.0315 0.5863 0.9871 4.500 0.6797 0.01073 0.00503 -0.0342 0.5429 0.9977 4.750 0.6951 0.01088 0.00505 -0.0324 0.5025 1.0000 5.000 0.7062 0.01118 0.00513 -0.0296 0.4587 1.0000 5.250 0.7212 0.01164 0.00536 -0.0275 0.4109 1.0000 5.500 0.7387 0.01219 0.00567 -0.0259 0.3668 1.0000 5.750 0.7578 0.01274 0.00603 -0.0246 0.3313 1.0000 6.000 0.7777 0.01330 0.00644 -0.0234 0.3023 1.0000 6.250 0.7978 0.01388 0.00690 -0.0223 0.2772 1.0000 6.500 0.8188 0.01442 0.00737 -0.0213 0.2534 1.0000 6.750 0.8392 0.01499 0.00785 -0.0203 0.2300 1.0000 7.000 0.8598 0.01553 0.00834 -0.0193 0.2046 1.0000 7.250 0.8797 0.01613 0.00886 -0.0182 0.1774 1.0000 7.500 0.8987 0.01683 0.00947 -0.0170 0.1522 1.0000 7.750 0.9157 0.01770 0.01018 -0.0156 0.1329 1.0000 8.000 0.9334 0.01854 0.01096 -0.0142 0.1174 1.0000 8.250 0.9502 0.01946 0.01181 -0.0128 0.1050 1.0000 8.500 0.9688 0.02020 0.01259 -0.0116 0.0947 1.0000 8.750 0.9860 0.02111 0.01355 -0.0102 0.0860 1.0000 9.000 1.0011 0.02224 0.01462 -0.0086 0.0782 1.0000 9.250 1.0186 0.02297 0.01545 -0.0073 0.0710 1.0000 9.500 1.0329 0.02419 0.01668 -0.0057 0.0646 1.0000 9.750 1.0473 0.02495 0.01750 -0.0041 0.0581 1.0000 10.000 1.0588 0.02623 0.01883 -0.0021 0.0524 1.0000 10.250 1.0697 0.02701 0.01968 -0.0001 0.0472 1.0000 10.500 1.0790 0.02855 0.02126 0.0019 0.0427 1.0000 10.750 1.0895 0.02963 0.02248 0.0038 0.0388 1.0000 11.000 1.0974 0.03115 0.02398 0.0055 0.0356 1.0000 11.250 1.1060 0.03292 0.02593 0.0073 0.0325 1.0000 11.500 1.1131 0.03423 0.02736 0.0089 0.0300 1.0000 11.750 1.1185 0.03581 0.02893 0.0103 0.0278 1.0000 12.000 1.1245 0.03845 0.03172 0.0117 0.0263 1.0000 12.250 1.1285 0.04058 0.03410 0.0132 0.0251 1.0000 12.500 1.1313 0.04292 0.03664 0.0144 0.0241 1.0000 12.750 1.1325 0.04549 0.03942 0.0154 0.0236 1.0000 13.000 1.1312 0.04803 0.04213 0.0161 0.0226 1.0000 13.250 1.1289 0.05092 0.04517 0.0166 0.0220 1.0000 13.500 1.1248 0.05411 0.04854 0.0168 0.0217 1.0000 13.750 1.1188 0.05765 0.05224 0.0167 0.0215 1.0000 14.000 1.1091 0.06181 0.05659 0.0161 0.0212 1.0000 14.250 1.0963 0.06650 0.06150 0.0149 0.0212 1.0000 14.500 1.0817 0.07166 0.06684 0.0131 0.0210 1.0000 14.750 1.0637 0.07762 0.07300 0.0105 0.0209 1.0000 15.000 1.0432 0.08438 0.08000 0.0067 0.0211 1.0000 15.250 1.0143 0.09347 0.08939 0.0009 0.0214 1.0000 15.500 0.9078 0.12333 0.11984 -0.0196 0.0244 1.0000