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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.5231 0.09180 0.08820 0.0090 1.0000 0.0315 -7.750 -0.5205 0.08776 0.08420 0.0057 1.0000 0.0318 -7.500 -0.5180 0.08333 0.07979 0.0009 1.0000 0.0321 -7.250 -0.5115 0.07869 0.07512 -0.0039 1.0000 0.0325 -7.000 -0.5030 0.07393 0.07030 -0.0086 1.0000 0.0330 -6.750 -0.4922 0.06911 0.06537 -0.0128 1.0000 0.0334 -6.250 -0.4680 0.05856 0.05445 -0.0177 1.0000 0.0294 -6.000 -0.4535 0.05603 0.05196 -0.0178 1.0000 0.0288 -5.750 -0.4375 0.05257 0.04838 -0.0186 1.0000 0.0283 -5.500 -0.4187 0.04834 0.04388 -0.0194 1.0000 0.0291 -5.250 -0.4003 0.04492 0.04026 -0.0196 1.0000 0.0292 -5.000 -0.3820 0.04214 0.03737 -0.0194 1.0000 0.0289 -4.750 -0.3620 0.03920 0.03425 -0.0192 0.9970 0.0287 -4.500 -0.3309 0.03572 0.03046 -0.0209 0.9759 0.0288 -4.250 -0.2993 0.03250 0.02690 -0.0222 0.9585 0.0298 -4.000 -0.2688 0.03123 0.02556 -0.0236 0.9432 0.0310 -3.750 -0.2389 0.02896 0.02301 -0.0242 0.9286 0.0319 -3.000 -0.1580 0.02314 0.01630 -0.0227 0.8867 0.0345 -2.750 -0.1326 0.02214 0.01516 -0.0221 0.8722 0.0355 -2.500 -0.1069 0.02078 0.01356 -0.0212 0.8578 0.0362 -2.250 -0.0808 0.01945 0.01198 -0.0202 0.8436 0.0371 -2.000 -0.0547 0.01829 0.01055 -0.0192 0.8295 0.0390 -1.750 -0.0289 0.01767 0.00987 -0.0186 0.8138 0.0399 -1.500 -0.0028 0.01689 0.00897 -0.0178 0.7971 0.0408 -1.250 0.0236 0.01614 0.00808 -0.0170 0.7794 0.0420 -1.000 0.0501 0.01551 0.00722 -0.0162 0.7606 0.0441 -0.750 0.0759 0.01496 0.00667 -0.0155 0.7370 0.0452 -0.500 0.1015 0.01451 0.00612 -0.0147 0.7092 0.0464 -0.250 0.1271 0.01410 0.00558 -0.0138 0.6801 0.0478 0.000 0.1530 0.01385 0.00514 -0.0130 0.6544 0.0501 0.250 0.1787 0.01346 0.00473 -0.0124 0.6313 0.0517 0.500 0.2045 0.01321 0.00441 -0.0118 0.6086 0.0533 0.750 0.2305 0.01301 0.00413 -0.0112 0.5871 0.0554 1.000 0.2567 0.01287 0.00390 -0.0107 0.5669 0.0581 1.250 0.2827 0.01266 0.00368 -0.0102 0.5483 0.0605 1.500 0.3091 0.01255 0.00352 -0.0098 0.5297 0.0631 1.750 0.3358 0.01251 0.00340 -0.0094 0.5113 0.0668 2.000 0.3624 0.01244 0.00329 -0.0090 0.4927 0.0707 2.250 0.3893 0.01246 0.00323 -0.0087 0.4736 0.0752 2.500 0.4161 0.01247 0.00320 -0.0083 0.4524 0.0821 2.750 0.4428 0.01254 0.00320 -0.0079 0.4287 0.0914 3.000 0.4621 0.01118 0.00320 -0.0068 0.4030 0.6270 3.250 0.5116 0.01067 0.00339 -0.0103 0.3465 1.0000 3.500 0.5354 0.01110 0.00349 -0.0096 0.2899 1.0000 3.750 0.5594 0.01155 0.00368 -0.0090 0.2531 1.0000 4.000 0.5839 0.01196 0.00391 -0.0085 0.2291 1.0000 4.250 0.6088 0.01232 0.00416 -0.0080 0.2105 1.0000 4.500 0.6339 0.01267 0.00441 -0.0075 0.1940 1.0000 4.750 0.6590 0.01302 0.00467 -0.0071 0.1789 1.0000 5.000 0.6843 0.01336 0.00494 -0.0066 0.1649 1.0000 5.250 0.7095 0.01371 0.00523 -0.0062 0.1518 1.0000 5.500 0.7347 0.01408 0.00554 -0.0058 0.1399 1.0000 5.750 0.7597 0.01448 0.00589 -0.0054 0.1294 1.0000 6.000 0.7846 0.01491 0.00626 -0.0050 0.1195 1.0000 6.250 0.8096 0.01531 0.00664 -0.0046 0.1111 1.0000 6.500 0.8341 0.01580 0.00707 -0.0041 0.1039 1.0000 6.750 0.8590 0.01622 0.00752 -0.0037 0.0973 1.0000 7.000 0.8830 0.01676 0.00800 -0.0033 0.0917 1.0000 7.250 0.9077 0.01721 0.00850 -0.0029 0.0868 1.0000 7.500 0.9316 0.01775 0.00903 -0.0024 0.0823 1.0000 7.750 0.9554 0.01831 0.00961 -0.0020 0.0785 1.0000 8.000 0.9793 0.01885 0.01019 -0.0015 0.0749 1.0000 8.250 1.0024 0.01947 0.01081 -0.0010 0.0717 1.0000 8.500 1.0252 0.02012 0.01150 -0.0005 0.0688 1.0000 8.750 1.0484 0.02073 0.01218 0.0000 0.0660 1.0000 9.000 1.0708 0.02138 0.01288 0.0005 0.0635 1.0000 9.250 1.0918 0.02222 0.01369 0.0011 0.0613 1.0000 9.500 1.1139 0.02292 0.01450 0.0017 0.0592 1.0000 9.750 1.1355 0.02365 0.01532 0.0023 0.0570 1.0000 10.000 1.1563 0.02443 0.01616 0.0029 0.0551 1.0000 10.250 1.1758 0.02532 0.01707 0.0036 0.0535 1.0000 10.500 1.1949 0.02629 0.01812 0.0043 0.0520 1.0000 10.750 1.2143 0.02719 0.01917 0.0051 0.0503 1.0000 11.000 1.2326 0.02813 0.02021 0.0058 0.0487 1.0000 11.250 1.2500 0.02910 0.02126 0.0066 0.0474 1.0000 11.500 1.2658 0.03017 0.02239 0.0075 0.0464 1.0000 11.750 1.2798 0.03145 0.02371 0.0085 0.0454 1.0000 12.000 1.2935 0.03269 0.02515 0.0095 0.0443 1.0000 12.250 1.3044 0.03398 0.02660 0.0107 0.0431 1.0000 12.500 1.3133 0.03535 0.02811 0.0119 0.0421 1.0000 12.750 1.3209 0.03684 0.02971 0.0129 0.0413 1.0000 13.000 1.3273 0.03848 0.03145 0.0137 0.0406 1.0000 13.250 1.3324 0.04033 0.03339 0.0142 0.0400 1.0000 13.500 1.3362 0.04243 0.03556 0.0146 0.0395 1.0000 13.750 1.3378 0.04491 0.03819 0.0146 0.0389 1.0000 14.000 1.3364 0.04787 0.04138 0.0142 0.0384 1.0000 14.250 1.3331 0.05122 0.04495 0.0133 0.0378 1.0000 14.500 1.3279 0.05497 0.04890 0.0120 0.0373 1.0000 14.750 1.3210 0.05916 0.05328 0.0101 0.0368 1.0000 15.000 1.3119 0.06381 0.05812 0.0079 0.0364 1.0000 15.250 1.3006 0.06898 0.06347 0.0051 0.0360 1.0000 15.500 1.2866 0.07475 0.06942 0.0019 0.0357 1.0000 15.750 1.2688 0.08138 0.07623 -0.0019 0.0355 1.0000 16.000 1.2457 0.08922 0.08426 -0.0065 0.0353 1.0000 16.250 1.2103 0.10010 0.09538 -0.0133 0.0353 1.0000