XFOIL Version 6.96 Calculated polar for: GOE 563 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3842 0.09258 0.09028 -0.0350 1.0000 0.0312 -10.250 -0.3883 0.08760 0.08532 -0.0365 1.0000 0.0312 -10.000 -0.4050 0.07986 0.07761 -0.0385 1.0000 0.0317 -9.750 -0.3975 0.07833 0.07609 -0.0371 1.0000 0.0325 -9.500 -0.3940 0.07580 0.07357 -0.0369 1.0000 0.0330 -9.250 -0.5293 0.04238 0.04022 -0.0554 1.0000 0.0245 -9.000 -0.5537 0.04076 0.03860 -0.0526 1.0000 0.0243 -8.750 -0.5870 0.03633 0.03410 -0.0498 1.0000 0.0238 -8.500 -0.6896 0.03727 0.03426 -0.0457 1.0000 0.0229 -8.250 -0.6916 0.02998 0.02616 -0.0455 0.9979 0.0241 -8.000 -0.6704 0.02528 0.02075 -0.0473 0.9948 0.0254 -7.750 -0.6425 0.02388 0.01927 -0.0485 0.9925 0.0264 -7.500 -0.6125 0.02315 0.01848 -0.0496 0.9898 0.0275 -7.250 -0.5815 0.02222 0.01739 -0.0508 0.9873 0.0290 -7.000 -0.5493 0.02116 0.01607 -0.0522 0.9852 0.0305 -6.750 -0.5174 0.01961 0.01418 -0.0536 0.9836 0.0316 -6.500 -0.4925 0.01762 0.01203 -0.0538 0.9801 0.0331 -6.250 -0.4619 0.01707 0.01144 -0.0546 0.9770 0.0346 -6.000 -0.4293 0.01637 0.01065 -0.0558 0.9747 0.0361 -5.750 -0.3955 0.01555 0.00969 -0.0572 0.9728 0.0373 -5.500 -0.3602 0.01501 0.00904 -0.0588 0.9714 0.0386 -5.250 -0.3249 0.01415 0.00806 -0.0605 0.9703 0.0397 -5.000 -0.3010 0.01302 0.00686 -0.0598 0.9649 0.0411 -4.750 -0.2682 0.01240 0.00622 -0.0610 0.9622 0.0427 -4.500 -0.2327 0.01193 0.00573 -0.0626 0.9602 0.0446 -4.250 -0.1968 0.01143 0.00519 -0.0643 0.9585 0.0461 -4.000 -0.1609 0.01097 0.00469 -0.0660 0.9567 0.0477 -3.750 -0.1329 0.01067 0.00435 -0.0659 0.9514 0.0489 -3.500 -0.1038 0.01010 0.00378 -0.0661 0.9467 0.0528 -3.250 -0.0711 0.00976 0.00344 -0.0670 0.9434 0.0569 -3.000 -0.0414 0.00944 0.00312 -0.0673 0.9391 0.0637 -2.750 -0.0156 0.00913 0.00293 -0.0667 0.9324 0.0853 -2.500 0.0142 0.00887 0.00274 -0.0670 0.9279 0.1135 -2.250 0.0406 0.00867 0.00260 -0.0665 0.9216 0.1310 -2.000 0.0676 0.00843 0.00245 -0.0662 0.9149 0.1531 -1.750 0.0943 0.00818 0.00230 -0.0658 0.9077 0.1897 -1.500 0.1191 0.00775 0.00212 -0.0651 0.8986 0.2600 -1.250 0.1413 0.00716 0.00203 -0.0640 0.8886 0.4201 -1.000 0.1646 0.00669 0.00193 -0.0629 0.8791 0.5393 -0.750 0.1841 0.00614 0.00188 -0.0609 0.8679 0.6875 -0.500 0.2033 0.00566 0.00192 -0.0584 0.8569 0.8431 -0.250 0.2498 0.00556 0.00197 -0.0617 0.8499 0.9414 0.000 0.2941 0.00558 0.00196 -0.0650 0.8404 0.9632 0.250 0.3360 0.00563 0.00195 -0.0678 0.8308 0.9770 0.500 0.3796 0.00567 0.00193 -0.0710 0.8205 0.9876 0.750 0.4235 0.00570 0.00189 -0.0743 0.8051 0.9961 1.000 0.4595 0.00572 0.00184 -0.0760 0.7887 1.0000 1.250 0.4820 0.00576 0.00180 -0.0747 0.7705 1.0000 1.500 0.5045 0.00582 0.00178 -0.0735 0.7508 1.0000 1.750 0.5270 0.00590 0.00177 -0.0722 0.7304 1.0000 2.000 0.5494 0.00600 0.00179 -0.0709 0.7073 1.0000 2.250 0.5717 0.00612 0.00182 -0.0696 0.6835 1.0000 2.500 0.5939 0.00627 0.00187 -0.0683 0.6576 1.0000 2.750 0.6155 0.00645 0.00194 -0.0668 0.6269 1.0000 3.000 0.6359 0.00670 0.00202 -0.0652 0.5842 1.0000 3.250 0.6553 0.00703 0.00213 -0.0634 0.5347 1.0000 3.500 0.6751 0.00738 0.00228 -0.0617 0.4872 1.0000 3.750 0.6940 0.00782 0.00247 -0.0599 0.4301 1.0000 4.250 0.7335 0.00869 0.00291 -0.0568 0.3355 1.0000 4.500 0.7550 0.00904 0.00313 -0.0556 0.3073 1.0000 4.750 0.7765 0.00939 0.00337 -0.0544 0.2786 1.0000 5.000 0.7980 0.00975 0.00361 -0.0532 0.2476 1.0000 5.250 0.8198 0.01011 0.00385 -0.0520 0.2188 1.0000 5.500 0.8411 0.01053 0.00412 -0.0508 0.1857 1.0000 5.750 0.8618 0.01101 0.00443 -0.0496 0.1527 1.0000 6.000 0.8829 0.01146 0.00477 -0.0484 0.1283 1.0000 6.250 0.9040 0.01193 0.00514 -0.0472 0.1074 1.0000 6.500 0.9241 0.01251 0.00555 -0.0459 0.0748 1.0000 6.750 0.9427 0.01326 0.00610 -0.0443 0.0486 1.0000 7.000 0.9632 0.01382 0.00664 -0.0430 0.0420 1.0000 7.250 0.9837 0.01438 0.00724 -0.0416 0.0382 1.0000 7.500 1.0045 0.01490 0.00781 -0.0404 0.0354 1.0000 7.750 1.0218 0.01573 0.00867 -0.0386 0.0321 1.0000 8.000 1.0412 0.01635 0.00935 -0.0372 0.0302 1.0000 8.250 1.0609 0.01692 0.00998 -0.0358 0.0283 1.0000 8.500 1.0792 0.01761 0.01070 -0.0343 0.0266 1.0000 8.750 1.0900 0.01899 0.01213 -0.0316 0.0247 1.0000 9.000 1.1096 0.01953 0.01275 -0.0303 0.0237 1.0000 9.250 1.1278 0.02016 0.01346 -0.0288 0.0225 1.0000 9.500 1.1452 0.02083 0.01417 -0.0272 0.0213 1.0000 9.750 1.1607 0.02163 0.01500 -0.0254 0.0204 1.0000 10.000 1.1704 0.02304 0.01647 -0.0228 0.0195 1.0000 10.250 1.1822 0.02427 0.01782 -0.0205 0.0188 1.0000 10.500 1.1956 0.02512 0.01877 -0.0183 0.0182 1.0000 10.750 1.2083 0.02600 0.01976 -0.0162 0.0176 1.0000 11.000 1.2201 0.02690 0.02074 -0.0140 0.0169 1.0000 11.250 1.2311 0.02779 0.02171 -0.0119 0.0163 1.0000 11.500 1.2412 0.02868 0.02263 -0.0098 0.0157 1.0000 11.750 1.2485 0.03022 0.02425 -0.0077 0.0152 1.0000 12.000 1.2523 0.03285 0.02705 -0.0054 0.0148 1.0000 12.250 1.2580 0.03410 0.02846 -0.0031 0.0145 1.0000 12.500 1.2621 0.03582 0.03036 -0.0010 0.0143 1.0000 12.750 1.2642 0.03765 0.03236 0.0010 0.0140 1.0000 13.000 1.2639 0.03990 0.03480 0.0029 0.0138 1.0000 13.250 1.2629 0.04210 0.03717 0.0045 0.0135 1.0000 13.500 1.2587 0.04477 0.04002 0.0059 0.0133 1.0000 13.750 1.2523 0.04782 0.04326 0.0069 0.0132 1.0000 14.000 1.2462 0.05090 0.04650 0.0074 0.0130 1.0000 14.250 1.2343 0.05499 0.05079 0.0074 0.0129 1.0000 14.500 1.2294 0.05822 0.05413 0.0068 0.0127 1.0000 14.750 1.2124 0.06353 0.05967 0.0054 0.0127 1.0000 15.000 1.2016 0.06821 0.06449 0.0036 0.0126 1.0000 15.250 1.1832 0.07457 0.07104 0.0005 0.0125 1.0000 15.500 1.1707 0.08034 0.07696 -0.0027 0.0125 1.0000 15.750 1.1277 0.09286 0.08980 -0.0103 0.0128 1.0000 16.000 1.1052 0.10212 0.09922 -0.0162 0.0127 1.0000 16.250 1.0333 0.12443 0.12189 -0.0305 0.0137 1.0000