XFOIL Version 6.96 Calculated polar for: MB253515 15.0% smoothed 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4184 0.10046 0.09353 -0.0545 1.0000 0.0582 -11.000 -0.4266 0.09463 0.08777 -0.0573 1.0000 0.0579 -10.750 -0.4406 0.08828 0.08148 -0.0608 1.0000 0.0575 -10.500 -0.4570 0.08263 0.07587 -0.0637 1.0000 0.0567 -10.250 -0.4785 0.07754 0.07082 -0.0657 1.0000 0.0559 -10.000 -0.5044 0.07339 0.06667 -0.0661 1.0000 0.0554 -9.750 -0.5314 0.07031 0.06365 -0.0643 1.0000 0.0548 -9.500 -0.5601 0.06825 0.06161 -0.0603 1.0000 0.0543 -9.250 -0.5885 0.06656 0.05992 -0.0552 1.0000 0.0541 -9.000 -0.6142 0.06496 0.05829 -0.0500 1.0000 0.0539 -8.750 -0.6376 0.06339 0.05664 -0.0449 1.0000 0.0538 -8.500 -0.6582 0.06166 0.05478 -0.0400 1.0000 0.0540 -8.250 -0.6526 0.05769 0.05037 -0.0407 0.9901 0.0546 -8.000 -0.6415 0.05377 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0.02535 0.01646 -0.0388 0.8449 0.6818 -3.000 -0.1580 0.02614 0.01733 -0.0355 0.8384 0.7603 -2.750 -0.1217 0.02696 0.01799 -0.0346 0.8328 0.8099 -2.500 -0.0748 0.02712 0.01784 -0.0376 0.8289 0.8281 -2.250 -0.0420 0.02738 0.01788 -0.0384 0.8216 0.8454 -2.000 0.0012 0.02752 0.01776 -0.0411 0.8162 0.8615 -1.750 0.0515 0.02753 0.01750 -0.0451 0.8125 0.8759 -1.500 0.0854 0.02779 0.01761 -0.0467 0.8042 0.8907 -1.250 0.1337 0.02776 0.01736 -0.0507 0.7994 0.9036 -1.000 0.1723 0.02788 0.01734 -0.0532 0.7924 0.9171 -0.750 0.2194 0.02786 0.01717 -0.0572 0.7862 0.9284 -0.500 0.2676 0.02771 0.01687 -0.0613 0.7808 0.9390 -0.250 0.3040 0.02778 0.01686 -0.0637 0.7720 0.9513 0.000 0.3473 0.02757 0.01653 -0.0670 0.7657 0.9619 0.250 0.3851 0.02754 0.01644 -0.0696 0.7562 0.9728 0.500 0.4271 0.02734 0.01617 -0.0729 0.7480 0.9822 0.750 0.4689 0.02709 0.01587 -0.0761 0.7396 0.9914 1.000 0.5048 0.02702 0.01579 -0.0785 0.7300 1.0000 1.250 0.5251 0.02688 0.01559 -0.0774 0.7225 1.0000 1.500 0.5312 0.02722 0.01593 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0.8306 0.03275 0.02214 -0.0288 0.5141 1.0000 7.000 0.8316 0.03388 0.02339 -0.0254 0.5032 1.0000 7.250 0.8487 0.03439 0.02400 -0.0239 0.4948 1.0000 7.500 0.8661 0.03489 0.02462 -0.0224 0.4864 1.0000 7.750 0.8679 0.03609 0.02592 -0.0193 0.4772 1.0000 8.000 0.8975 0.03614 0.02613 -0.0192 0.4706 1.0000 8.250 0.8901 0.03786 0.02794 -0.0153 0.4608 1.0000 8.500 0.9256 0.03767 0.02798 -0.0158 0.4552 1.0000 8.750 0.9098 0.04006 0.03046 -0.0116 0.4453 1.0000 9.000 0.9477 0.03971 0.03035 -0.0121 0.4403 1.0000 9.250 0.9246 0.04285 0.03357 -0.0080 0.4302 1.0000 9.500 0.9563 0.04242 0.03337 -0.0075 0.4229 1.0000 9.750 0.9663 0.04224 0.03331 -0.0047 0.4061 1.0000 10.000 0.9837 0.04033 0.03140 -0.0013 0.3780 1.0000 10.250 0.9794 0.04137 0.03247 0.0018 0.3576 1.0000 10.500 0.9777 0.04220 0.03329 0.0046 0.3333 1.0000 10.750 0.9706 0.04407 0.03523 0.0068 0.3107 1.0000 11.000 0.9615 0.04638 0.03761 0.0087 0.2845 1.0000 11.250 0.9501 0.04917 0.04043 0.0101 0.2508 1.0000 11.500 0.9371 0.05229 0.04329 0.0114 0.1843 1.0000 11.750 0.9176 0.05626 0.04650 0.0124 0.1174 1.0000 12.000 0.8980 0.06106 0.05094 0.0126 0.0942 1.0000 12.250 0.8832 0.06568 0.05543 0.0124 0.0832 1.0000 12.500 0.8710 0.07019 0.05989 0.0121 0.0766 1.0000 12.750 0.8621 0.07443 0.06414 0.0117 0.0711 1.0000 13.000 0.8549 0.07850 0.06825 0.0112 0.0666 1.0000 13.250 0.8479 0.08258 0.07226 0.0107 0.0627 1.0000 13.500 0.8475 0.08581 0.07562 0.0104 0.0585 1.0000 13.750 0.8476 0.08898 0.07882 0.0102 0.0550 1.0000 14.000 0.8485 0.09184 0.08164 0.0102 0.0522 1.0000 14.250 0.8567 0.09377 0.08372 0.0109 0.0500 1.0000 14.500 0.8658 0.09568 0.08580 0.0114 0.0472 1.0000 14.750 0.8747 0.09764 0.08787 0.0119 0.0447 1.0000 15.000 0.8851 0.09929 0.08953 0.0126 0.0422 1.0000 15.250 0.9013 0.10031 0.09062 0.0140 0.0402 1.0000 15.500 0.9129 0.10249 0.09311 0.0146 0.0392 1.0000 15.750 0.9200 0.10545 0.09634 0.0145 0.0384 1.0000 16.000 0.9211 0.10934 0.10050 0.0135 0.0376 1.0000 16.250 0.9185 0.11388 0.10529 0.0120 0.0369 1.0000 16.500 0.9121 0.11911 0.11075 0.0099 0.0364 1.0000 16.750 0.9034 0.12497 0.11683 0.0071 0.0364 1.0000 17.000 0.8913 0.13168 0.12374 0.0037 0.0361 1.0000 17.250 0.8763 0.13942 0.13168 -0.0006 0.0362 1.0000 17.500 0.8585 0.14844 0.14087 -0.0057 0.0369 1.0000