XFOIL Version 6.96 Calculated polar for: HQ 1.0/9 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.750 -0.4899 0.15053 0.14902 0.0151 1.0000 0.0071 -13.500 -0.4892 0.14788 0.14636 0.0133 1.0000 0.0078 -8.250 -0.7299 0.02545 0.02207 -0.0341 1.0000 0.0059 -7.750 -0.7016 0.02033 0.01630 -0.0310 1.0000 0.0059 -7.500 -0.6831 0.01879 0.01454 -0.0296 1.0000 0.0057 -7.250 -0.6655 0.01707 0.01261 -0.0280 1.0000 0.0057 -7.000 -0.6473 0.01575 0.01111 -0.0264 1.0000 0.0057 -6.750 -0.6265 0.01389 0.00904 -0.0255 0.9991 0.0058 -6.500 -0.5943 0.01244 0.00742 -0.0269 0.9958 0.0063 -6.250 -0.5609 0.01178 0.00670 -0.0284 0.9923 0.0071 -6.000 -0.5279 0.01117 0.00602 -0.0298 0.9880 0.0078 -5.750 -0.4935 0.01056 0.00534 -0.0314 0.9844 0.0084 -5.500 -0.4599 0.01011 0.00483 -0.0327 0.9792 0.0089 -5.250 -0.4281 0.00925 0.00382 -0.0337 0.9715 0.0105 -5.000 -0.3970 0.00887 0.00342 -0.0345 0.9619 0.0132 -4.750 -0.3681 0.00844 0.00294 -0.0347 0.9498 0.0184 -4.500 -0.3413 0.00812 0.00264 -0.0345 0.9356 0.0318 -4.250 -0.3151 0.00790 0.00242 -0.0341 0.9215 0.0427 -4.000 -0.2890 0.00770 0.00222 -0.0337 0.9085 0.0547 -3.500 -0.2370 0.00724 0.00182 -0.0330 0.8845 0.1014 -3.250 -0.2118 0.00681 0.00163 -0.0327 0.8728 0.1719 -3.000 -0.1858 0.00650 0.00147 -0.0324 0.8616 0.2267 -2.750 -0.1601 0.00609 0.00129 -0.0322 0.8511 0.3063 -2.500 -0.1350 0.00560 0.00113 -0.0319 0.8415 0.4187 -2.250 -0.1090 0.00528 0.00104 -0.0316 0.8324 0.5006 -2.000 -0.0820 0.00512 0.00099 -0.0315 0.8239 0.5498 -1.750 -0.0548 0.00503 0.00095 -0.0313 0.8147 0.5844 -1.500 -0.0277 0.00495 0.00091 -0.0310 0.8037 0.6195 -1.250 -0.0003 0.00489 0.00088 -0.0309 0.7926 0.6444 -1.000 0.0272 0.00486 0.00087 -0.0307 0.7825 0.6666 -0.750 0.0546 0.00484 0.00086 -0.0305 0.7722 0.6880 -0.500 0.0821 0.00484 0.00084 -0.0304 0.7605 0.7037 -0.250 0.1098 0.00483 0.00083 -0.0302 0.7488 0.7183 0.000 0.1375 0.00483 0.00084 -0.0301 0.7383 0.7317 0.250 0.1652 0.00483 0.00084 -0.0300 0.7270 0.7436 0.500 0.1928 0.00484 0.00085 -0.0299 0.7154 0.7555 0.750 0.2204 0.00486 0.00087 -0.0298 0.7033 0.7671 1.000 0.2479 0.00488 0.00089 -0.0296 0.6906 0.7798 1.250 0.2753 0.00490 0.00091 -0.0295 0.6766 0.7926 1.500 0.3027 0.00494 0.00095 -0.0293 0.6598 0.8042 1.750 0.3299 0.00499 0.00098 -0.0291 0.6403 0.8154 2.000 0.3569 0.00505 0.00102 -0.0289 0.6197 0.8270 2.250 0.3835 0.00513 0.00107 -0.0286 0.5923 0.8398 2.500 0.4092 0.00528 0.00114 -0.0281 0.5486 0.8539 2.750 0.4348 0.00544 0.00123 -0.0276 0.5093 0.8702 3.000 0.4595 0.00562 0.00133 -0.0270 0.4652 0.8911 3.250 0.4829 0.00586 0.00147 -0.0260 0.4089 0.9219 3.500 0.5133 0.00623 0.00166 -0.0268 0.3376 0.9653 3.750 0.5519 0.00668 0.00187 -0.0295 0.2773 0.9947 4.000 0.5795 0.00700 0.00205 -0.0297 0.2431 1.0000 4.250 0.6047 0.00732 0.00223 -0.0294 0.2099 1.0000 4.500 0.6302 0.00761 0.00242 -0.0291 0.1814 1.0000 4.750 0.6555 0.00795 0.00264 -0.0287 0.1481 1.0000 5.000 0.6798 0.00842 0.00291 -0.0283 0.1078 1.0000 5.250 0.7043 0.00889 0.00322 -0.0279 0.0762 1.0000 5.500 0.7295 0.00925 0.00350 -0.0275 0.0582 1.0000 5.750 0.7548 0.00961 0.00379 -0.0272 0.0441 1.0000 6.000 0.7798 0.01001 0.00413 -0.0268 0.0308 1.0000 6.250 0.8047 0.01042 0.00449 -0.0264 0.0208 1.0000 6.500 0.8287 0.01099 0.00502 -0.0258 0.0114 1.0000 6.750 0.8534 0.01144 0.00548 -0.0253 0.0085 1.0000 7.000 0.8767 0.01215 0.00628 -0.0246 0.0068 1.0000 7.250 0.9012 0.01261 0.00680 -0.0241 0.0063 1.0000 7.500 0.9252 0.01314 0.00740 -0.0235 0.0056 1.0000 7.750 0.9486 0.01374 0.00806 -0.0229 0.0050 1.0000 8.000 0.9694 0.01473 0.00916 -0.0218 0.0046 1.0000 8.250 0.9889 0.01589 0.01046 -0.0206 0.0044 1.0000 8.500 1.0051 0.01755 0.01232 -0.0189 0.0043 1.0000 8.750 1.0226 0.01905 0.01398 -0.0175 0.0042 1.0000 9.000 1.0393 0.02071 0.01581 -0.0160 0.0042 1.0000 9.250 1.0547 0.02260 0.01790 -0.0144 0.0042 1.0000 9.500 1.0666 0.02503 0.02058 -0.0126 0.0042 1.0000 9.750 1.0781 0.02719 0.02299 -0.0108 0.0041 1.0000 10.000 1.0951 0.02807 0.02403 -0.0096 0.0040 1.0000 10.250 1.1050 0.02995 0.02611 -0.0078 0.0040 1.0000 10.500 1.1076 0.03249 0.02890 -0.0053 0.0040 1.0000 10.750 1.1005 0.03541 0.03210 -0.0018 0.0040 1.0000 11.000 1.0811 0.03862 0.03555 0.0026 0.0040 1.0000 11.250 1.0725 0.04095 0.03804 0.0049 0.0040 1.0000 11.500 1.0563 0.04443 0.04172 0.0064 0.0040 1.0000 11.750 1.0312 0.04967 0.04713 0.0064 0.0042 1.0000 12.000 1.0140 0.05449 0.05211 0.0050 0.0042 1.0000 12.250 1.0124 0.05770 0.05541 0.0034 0.0042 1.0000 12.500 0.9878 0.06528 0.06317 -0.0013 0.0042 1.0000 12.750 0.9729 0.07241 0.07043 -0.0064 0.0042 1.0000 13.000 0.9632 0.07947 0.07759 -0.0115 0.0042 1.0000 13.250 0.9505 0.08811 0.08634 -0.0175 0.0043 1.0000