XFOIL Version 6.96 Calculated polar for: GIII BL450 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4448 0.11619 0.11459 0.0151 1.0000 0.0171 -10.250 -0.4485 0.11120 0.10960 0.0128 1.0000 0.0180 -10.000 -0.5758 0.11798 0.11629 0.0281 1.0000 0.0164 -9.750 -0.5714 0.11438 0.11270 0.0265 1.0000 0.0168 -9.500 -0.5675 0.11059 0.10892 0.0247 1.0000 0.0173 -8.250 -0.5710 0.08541 0.08380 0.0058 1.0000 0.0183 -8.000 -0.5667 0.08141 0.07981 0.0019 1.0000 0.0183 -7.750 -0.5587 0.07761 0.07599 -0.0013 1.0000 0.0184 -7.500 -0.5494 0.07383 0.07219 -0.0043 1.0000 0.0186 -7.250 -0.5386 0.07009 0.06841 -0.0072 1.0000 0.0187 -7.000 -0.5263 0.06641 0.06470 -0.0097 1.0000 0.0189 -6.750 -0.5123 0.06285 0.06108 -0.0120 1.0000 0.0193 -6.500 -0.4945 0.05570 0.05368 -0.0165 1.0000 0.0211 -6.250 -0.4780 0.05059 0.04840 -0.0179 1.0000 0.0212 -5.000 -0.3726 0.03735 0.03459 -0.0214 0.9119 0.0228 -4.750 -0.3468 0.03200 0.02873 -0.0201 0.8998 0.0246 -4.500 -0.3279 0.02873 0.02527 -0.0198 0.8891 0.0250 -4.250 -0.3045 0.02787 0.02434 -0.0196 0.8784 0.0253 -4.000 -0.2887 0.01470 0.00985 -0.0165 0.8700 0.0251 -3.750 -0.2615 0.01513 0.01029 -0.0163 0.8594 0.0253 -3.500 -0.2340 0.01551 0.01070 -0.0161 0.8481 0.0256 -3.250 -0.2071 0.01532 0.01047 -0.0159 0.8375 0.0260 -3.000 -0.1823 0.01199 0.00665 -0.0148 0.8270 0.0281 -2.750 -0.1557 0.01116 0.00570 -0.0143 0.8153 0.0290 -2.500 -0.1283 0.01116 0.00569 -0.0141 0.8008 0.0296 -2.250 -0.1010 0.01101 0.00549 -0.0137 0.7818 0.0303 -2.000 -0.0742 0.01054 0.00489 -0.0133 0.7594 0.0312 -1.750 -0.0474 0.01010 0.00431 -0.0128 0.7336 0.0322 -1.500 -0.0212 0.00962 0.00369 -0.0122 0.7032 0.0332 -1.250 0.0059 0.00957 0.00356 -0.0119 0.6715 0.0340 -1.000 0.0331 0.00948 0.00338 -0.0116 0.6434 0.0349 -0.500 0.0875 0.00919 0.00288 -0.0110 0.5926 0.0369 -0.250 0.1142 0.00891 0.00252 -0.0106 0.5709 0.0381 0.000 0.1416 0.00886 0.00243 -0.0104 0.5493 0.0393 0.250 0.1692 0.00879 0.00230 -0.0102 0.5310 0.0406 0.500 0.1968 0.00871 0.00217 -0.0100 0.5151 0.0419 0.750 0.2247 0.00869 0.00211 -0.0098 0.5008 0.0428 1.000 0.2518 0.00846 0.00186 -0.0095 0.4868 0.0449 1.250 0.2796 0.00844 0.00181 -0.0094 0.4727 0.0468 1.500 0.3074 0.00843 0.00175 -0.0092 0.4571 0.0484 1.750 0.3349 0.00837 0.00164 -0.0090 0.4385 0.0503 2.000 0.3626 0.00836 0.00159 -0.0088 0.4190 0.0529 2.250 0.3902 0.00841 0.00158 -0.0087 0.3959 0.0554 2.500 0.4177 0.00848 0.00155 -0.0085 0.3672 0.0575 2.750 0.4446 0.00865 0.00156 -0.0083 0.3196 0.0615 3.000 0.4708 0.00901 0.00167 -0.0081 0.2605 0.0650 3.250 0.4978 0.00920 0.00176 -0.0079 0.2323 0.0712 3.500 0.5251 0.00932 0.00187 -0.0078 0.2134 0.0941 3.750 0.5366 0.00734 0.00202 -0.0048 0.2017 0.9116 4.000 0.5910 0.00753 0.00219 -0.0104 0.1794 0.9991 4.250 0.6187 0.00773 0.00230 -0.0103 0.1650 1.0000 4.500 0.6443 0.00794 0.00243 -0.0098 0.1513 1.0000 4.750 0.6700 0.00814 0.00257 -0.0094 0.1390 1.0000 5.000 0.6958 0.00837 0.00272 -0.0089 0.1271 1.0000 5.250 0.7217 0.00860 0.00289 -0.0085 0.1162 1.0000 5.500 0.7476 0.00886 0.00308 -0.0081 0.1061 1.0000 5.750 0.7737 0.00911 0.00327 -0.0078 0.0976 1.0000 6.000 0.7999 0.00934 0.00347 -0.0074 0.0902 1.0000 6.250 0.8258 0.00964 0.00371 -0.0071 0.0827 1.0000 6.500 0.8523 0.00986 0.00392 -0.0068 0.0784 1.0000 6.750 0.8781 0.01020 0.00420 -0.0065 0.0724 1.0000 7.000 0.9046 0.01040 0.00442 -0.0063 0.0696 1.0000 7.250 0.9307 0.01070 0.00468 -0.0060 0.0660 1.0000 7.500 0.9565 0.01103 0.00500 -0.0057 0.0625 1.0000 7.750 0.9829 0.01127 0.00525 -0.0055 0.0602 1.0000 8.000 1.0088 0.01158 0.00555 -0.0052 0.0574 1.0000 8.250 1.0341 0.01200 0.00596 -0.0049 0.0545 1.0000 8.500 1.0603 0.01224 0.00623 -0.0047 0.0529 1.0000 8.750 1.0861 0.01254 0.00654 -0.0045 0.0509 1.0000 9.000 1.1111 0.01296 0.00694 -0.0042 0.0484 1.0000 9.250 1.1363 0.01336 0.00736 -0.0038 0.0468 1.0000 9.500 1.1619 0.01366 0.00770 -0.0036 0.0454 1.0000 9.750 1.1871 0.01401 0.00806 -0.0033 0.0439 1.0000 10.000 1.2115 0.01447 0.00852 -0.0030 0.0421 1.0000 10.250 1.2355 0.01497 0.00905 -0.0026 0.0406 1.0000 10.500 1.2604 0.01532 0.00944 -0.0023 0.0395 1.0000 10.750 1.2849 0.01571 0.00986 -0.0020 0.0384 1.0000 11.000 1.3087 0.01617 0.01034 -0.0017 0.0372 1.0000 11.250 1.3307 0.01686 0.01104 -0.0011 0.0358 1.0000 11.500 1.3536 0.01739 0.01163 -0.0007 0.0349 1.0000 11.750 1.3771 0.01781 0.01211 -0.0003 0.0341 1.0000 12.000 1.4001 0.01828 0.01262 0.0001 0.0332 1.0000 12.250 1.4223 0.01883 0.01319 0.0006 0.0323 1.0000 12.500 1.4429 0.01951 0.01391 0.0012 0.0314 1.0000 12.750 1.4596 0.02058 0.01503 0.0021 0.0304 1.0000 13.000 1.4808 0.02111 0.01563 0.0027 0.0300 1.0000 13.250 1.5007 0.02173 0.01633 0.0034 0.0294 1.0000 13.500 1.5197 0.02241 0.01707 0.0041 0.0288 1.0000 13.750 1.5378 0.02310 0.01782 0.0049 0.0281 1.0000 14.000 1.5542 0.02390 0.01866 0.0057 0.0275 1.0000 14.250 1.5656 0.02490 0.01972 0.0072 0.0270 1.0000 14.500 1.5695 0.02640 0.02129 0.0090 0.0264 1.0000 14.750 1.5726 0.02811 0.02310 0.0103 0.0260 1.0000 15.000 1.5822 0.02941 0.02450 0.0109 0.0257 1.0000 15.250 1.5901 0.03096 0.02615 0.0114 0.0254 1.0000 15.500 1.5963 0.03278 0.02808 0.0116 0.0251 1.0000 15.750 1.6009 0.03489 0.03029 0.0116 0.0248 1.0000 16.000 1.6042 0.03728 0.03277 0.0112 0.0245 1.0000 16.250 1.6061 0.03999 0.03558 0.0105 0.0242 1.0000 16.500 1.6060 0.04309 0.03878 0.0094 0.0239 1.0000 16.750 1.6037 0.04661 0.04241 0.0080 0.0236 1.0000 17.000 1.5981 0.05070 0.04660 0.0062 0.0233 1.0000 17.250 1.5882 0.05545 0.05146 0.0040 0.0231 1.0000 17.500 1.5741 0.06088 0.05700 0.0015 0.0230 1.0000 17.750 1.5559 0.06694 0.06318 -0.0013 0.0228 1.0000 18.000 1.5350 0.07353 0.06989 -0.0043 0.0227 1.0000 18.250 1.5120 0.08065 0.07714 -0.0078 0.0226 1.0000 18.500 1.4881 0.08816 0.08477 -0.0115 0.0225 1.0000 18.750 1.4632 0.09598 0.09272 -0.0153 0.0223 1.0000