XFOIL Version 6.96 Calculated polar for: GIII BL45 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6060 0.09425 0.08960 -0.0069 1.0000 0.1294 -9.000 -0.6492 0.08779 0.08320 -0.0172 1.0000 0.1328 -8.750 -0.6738 0.08287 0.07824 -0.0190 1.0000 0.1346 -8.500 -0.6376 0.07924 0.07471 -0.0159 1.0000 0.1396 -8.250 -0.6605 0.07532 0.07069 -0.0179 1.0000 0.1459 -8.000 -0.6665 0.07065 0.06598 -0.0179 1.0000 0.1505 -7.750 -0.6594 0.06747 0.06278 -0.0170 1.0000 0.1583 -7.500 -0.6939 0.05125 0.04527 -0.0176 1.0000 0.0813 -7.250 -0.6932 0.04473 0.03777 -0.0134 1.0000 0.0651 -7.000 -0.6840 0.04129 0.03394 -0.0109 1.0000 0.0652 -6.750 -0.6729 0.03791 0.03018 -0.0084 1.0000 0.0651 -6.500 -0.6596 0.03453 0.02644 -0.0060 1.0000 0.0645 -6.250 -0.6443 0.03171 0.02320 -0.0035 1.0000 0.0646 -6.000 -0.6270 0.02951 0.02054 -0.0012 1.0000 0.0655 -5.750 -0.6084 0.02701 0.01797 0.0001 1.0000 0.0698 -5.500 -0.5882 0.02547 0.01626 0.0017 1.0000 0.0743 -5.250 -0.5662 0.02389 0.01437 0.0034 1.0000 0.0783 -5.000 -0.5453 0.02224 0.01282 0.0046 1.0000 0.0859 -4.750 -0.5254 0.02098 0.01154 0.0062 1.0000 0.0963 -4.500 -0.5068 0.01981 0.01042 0.0080 1.0000 0.1101 -4.250 -0.4897 0.01887 0.00954 0.0100 1.0000 0.1336 -4.000 -0.4751 0.01767 0.00868 0.0123 1.0000 0.1731 -3.750 -0.4627 0.01625 0.00783 0.0148 1.0000 0.2501 -3.500 -0.4566 0.01413 0.00719 0.0182 1.0000 0.4678 -3.250 -0.4395 0.01376 0.00811 0.0236 1.0000 0.7942 -3.000 -0.4102 0.01465 0.00891 0.0262 1.0000 0.8752 -2.750 -0.3393 0.01606 0.00996 0.0214 1.0000 0.9248 -2.500 -0.2241 0.01687 0.01027 0.0067 1.0000 0.9483 -2.250 -0.1519 0.01688 0.01002 -0.0017 1.0000 0.9654 -2.000 -0.0642 0.01657 0.00944 -0.0133 1.0000 0.9847 -1.750 0.0129 0.01594 0.00863 -0.0236 1.0000 1.0000 -1.500 0.0184 0.01586 0.00854 -0.0211 1.0000 1.0000 -1.250 0.0154 0.01591 0.00859 -0.0172 1.0000 1.0000 -1.000 0.0068 0.01604 0.00871 -0.0125 1.0000 1.0000 -0.750 -0.0037 0.01620 0.00886 -0.0075 1.0000 1.0000 -0.500 -0.0143 0.01639 0.00903 -0.0026 1.0000 1.0000 -0.250 0.0312 0.01651 0.00909 -0.0075 0.9913 1.0000 0.000 0.0868 0.01658 0.00913 -0.0141 0.9811 1.0000 0.250 0.1420 0.01660 0.00915 -0.0204 0.9704 1.0000 0.500 0.2033 0.01646 0.00903 -0.0275 0.9582 1.0000 0.750 0.2755 0.01596 0.00858 -0.0358 0.9421 1.0000 1.000 0.3239 0.01553 0.00819 -0.0392 0.9197 1.0000 1.250 0.3573 0.01525 0.00793 -0.0397 0.8985 1.0000 1.500 0.3806 0.01515 0.00784 -0.0383 0.8773 1.0000 1.750 0.4016 0.01506 0.00779 -0.0365 0.8570 1.0000 2.000 0.4219 0.01498 0.00770 -0.0344 0.8380 1.0000 2.250 0.4411 0.01495 0.00770 -0.0324 0.8165 1.0000 2.500 0.4611 0.01486 0.00762 -0.0303 0.7968 1.0000 2.750 0.4811 0.01480 0.00761 -0.0283 0.7747 1.0000 3.000 0.5015 0.01468 0.00750 -0.0262 0.7528 1.0000 3.250 0.5217 0.01460 0.00744 -0.0242 0.7275 1.0000 3.500 0.5422 0.01452 0.00736 -0.0222 0.7005 1.0000 3.750 0.5628 0.01447 0.00732 -0.0201 0.6698 1.0000 4.000 0.5830 0.01448 0.00727 -0.0180 0.6319 1.0000 4.250 0.6025 0.01459 0.00726 -0.0158 0.5830 1.0000 4.500 0.6210 0.01490 0.00732 -0.0135 0.5202 1.0000 4.750 0.6390 0.01546 0.00756 -0.0114 0.4530 1.0000 5.000 0.6578 0.01614 0.00794 -0.0097 0.4058 1.0000 5.250 0.6780 0.01681 0.00846 -0.0084 0.3738 1.0000 5.500 0.6989 0.01748 0.00902 -0.0072 0.3511 1.0000 5.750 0.7199 0.01814 0.00964 -0.0060 0.3313 1.0000 6.000 0.7389 0.01874 0.01017 -0.0046 0.3078 1.0000 6.250 0.7564 0.01928 0.01069 -0.0030 0.2820 1.0000 6.500 0.7741 0.01984 0.01125 -0.0014 0.2597 1.0000 6.750 0.7905 0.02032 0.01174 0.0003 0.2353 1.0000 7.000 0.8049 0.02069 0.01221 0.0024 0.2047 1.0000 7.250 0.8142 0.02137 0.01280 0.0053 0.1293 1.0000 7.500 0.8233 0.02303 0.01404 0.0083 0.0867 1.0000 7.750 0.8345 0.02463 0.01552 0.0110 0.0736 1.0000 8.000 0.8481 0.02618 0.01709 0.0133 0.0647 1.0000 8.250 0.8627 0.02832 0.01909 0.0152 0.0594 1.0000 8.500 0.8826 0.03011 0.02110 0.0168 0.0563 1.0000 8.750 0.9018 0.03211 0.02329 0.0183 0.0532 1.0000 9.000 0.9194 0.03427 0.02547 0.0195 0.0497 1.0000 9.250 0.9359 0.03781 0.02924 0.0207 0.0476 1.0000 9.500 0.9481 0.04050 0.03235 0.0228 0.0471 1.0000 9.750 0.9565 0.04359 0.03586 0.0250 0.0469 1.0000 10.000 0.9606 0.04704 0.03971 0.0274 0.0470 1.0000 10.250 0.9608 0.05084 0.04387 0.0296 0.0473 1.0000 10.500 0.9580 0.05516 0.04850 0.0317 0.0477 1.0000 10.750 0.9549 0.05901 0.05265 0.0336 0.0483 1.0000 11.000 0.9442 0.06150 0.05547 0.0363 0.0488 1.0000 11.250 0.9158 0.06450 0.05884 0.0390 0.0499 1.0000 11.500 0.8683 0.07043 0.06515 0.0378 0.0513 1.0000 11.750 0.8279 0.07847 0.07343 0.0325 0.0523 1.0000 12.000 0.7802 0.09136 0.08641 0.0222 0.0541 1.0000 12.250 0.7490 0.10453 0.09955 0.0139 0.0568 1.0000 12.500 0.7414 0.11118 0.10616 0.0114 0.0585 1.0000