XFOIL Version 6.94 Calculated polar for: HORSTMANN AND QUAST HQ-300 GD(M 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.5437 0.01147 0.00610 -0.1049 0.6382 0.7995 0.500 0.5959 0.01173 0.00632 -0.1039 0.6315 0.8065 1.000 0.6542 0.01201 0.00651 -0.1046 0.6245 0.8152 1.500 0.7155 0.01200 0.00650 -0.1063 0.6162 0.8209 2.000 0.7695 0.01209 0.00651 -0.1060 0.6085 0.8248 2.500 0.8247 0.01213 0.00662 -0.1062 0.6004 0.8289 3.000 0.8824 0.01222 0.00668 -0.1070 0.5925 0.8334 3.500 0.9423 0.01232 0.00682 -0.1085 0.5840 0.8376 4.000 1.0040 0.01244 0.00692 -0.1104 0.5750 0.8424 4.500 1.0639 0.01250 0.00706 -0.1119 0.5650 0.8456 5.500 1.1708 0.01260 0.00729 -0.1119 0.5421 0.8525 6.000 1.2247 0.01274 0.00751 -0.1121 0.5282 0.8564 6.500 1.2792 0.01293 0.00777 -0.1125 0.5120 0.8600 7.000 1.3332 0.01320 0.00809 -0.1130 0.4921 0.8636 7.500 1.3848 0.01364 0.00854 -0.1131 0.4678 0.8672 8.000 1.4308 0.01416 0.00907 -0.1123 0.4370 0.8708 8.500 1.4656 0.01498 0.00983 -0.1094 0.4007 0.8744 9.000 1.4861 0.01626 0.01099 -0.1042 0.3613 0.8785 9.500 1.5013 0.01811 0.01273 -0.0991 0.3198 0.8831 10.000 1.5164 0.02052 0.01504 -0.0952 0.2830 0.8879 10.500 1.5330 0.02327 0.01775 -0.0922 0.2548 0.8918 11.000 1.5463 0.02639 0.02085 -0.0895 0.2266 0.8954 11.500 1.5553 0.02987 0.02433 -0.0865 0.1996 0.8993 12.000 1.5595 0.03397 0.02841 -0.0837 0.1738 0.9032 12.500 1.5602 0.03859 0.03300 -0.0810 0.1485 0.9070 13.000 1.5579 0.04372 0.03809 -0.0787 0.1228 0.9112 13.500 1.5507 0.04971 0.04400 -0.0767 0.0957 0.9144 14.000 1.5384 0.05651 0.05070 -0.0750 0.0666 0.9168 14.500 1.5202 0.06413 0.05824 -0.0736 0.0434 0.9204 15.000 1.5051 0.07176 0.06591 -0.0726 0.0323 0.9238 15.500 1.4953 0.07913 0.07342 -0.0723 0.0272 0.9272 16.000 1.4863 0.08671 0.08116 -0.0726 0.0242 0.9306 16.500 1.4749 0.09488 0.08949 -0.0735 0.0222 0.9339 17.000 1.4662 0.10295 0.09775 -0.0748 0.0205 0.9372 17.500 1.4545 0.11162 0.10660 -0.0767 0.0193 0.9412 18.000 1.4448 0.11996 0.11514 -0.0788 0.0181 0.9467 18.500 1.4317 0.12900 0.12433 -0.0817 0.0172 0.9519 19.000 1.4269 0.13697 0.13251 -0.0847 0.0162 0.9581 20.000 1.4158 0.15334 0.14918 -0.0926 0.0146 1.0000 20.500 1.4168 0.16131 0.15733 -0.0975 0.0138 1.0000 21.000 1.4189 0.16890 0.16499 -0.1025 0.0130 1.0000 21.500 1.4211 0.17664 0.17292 -0.1079 0.0122 1.0000 22.000 1.4239 0.18431 0.18072 -0.1135 0.0114 1.0000 22.500 1.4280 0.19147 0.18797 -0.1189 0.0107 1.0000 23.000 1.4282 0.19992 0.19664 -0.1255 0.0099 1.0000 23.500 1.4331 0.20700 0.20378 -0.1314 0.0092 1.0000 24.500 1.4298 0.22485 0.22204 -0.1464 0.0079 1.0000 25.000 1.4363 0.23121 0.22841 -0.1523 0.0074 1.0000 25.500 1.4263 0.24286 0.24039 -0.1623 0.0070 1.0000 26.000 1.4154 0.25524 0.25306 -0.1730 0.0067 1.0000 26.500 1.3952 0.27181 0.26996 -0.1868 0.0065 1.0000