XFOIL Version 6.96 Calculated polar for: GOE 416A 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 ------ -------- --------- --------- -------- -------- -------- -11.250 -0.5222 0.08503 0.08345 -0.0179 1.0000 0.0090 -11.000 -0.5407 0.07723 0.07560 -0.0218 1.0000 0.0090 -10.750 -0.6487 0.08844 0.08688 -0.0081 1.0000 0.0081 -10.500 -0.6702 0.07802 0.07640 -0.0164 1.0000 0.0078 -10.250 -0.6911 0.06984 0.06811 -0.0234 1.0000 0.0076 -10.000 -0.7100 0.06306 0.06122 -0.0296 1.0000 0.0075 -9.750 -0.7272 0.05753 0.05557 -0.0350 1.0000 0.0075 -9.500 -0.7394 0.05340 0.05128 -0.0374 1.0000 0.0075 -9.250 -0.7418 0.04946 0.04716 -0.0385 1.0000 0.0078 -9.000 -0.7285 0.04706 0.04444 -0.0380 1.0000 0.0089 -8.750 -0.7217 0.04413 0.04123 -0.0379 1.0000 0.0090 -8.500 -0.7132 0.04091 0.03773 -0.0377 1.0000 0.0091 -8.250 -0.7017 0.03784 0.03437 -0.0373 1.0000 0.0091 -8.000 -0.6998 0.03011 0.02620 -0.0367 1.0000 0.0095 -7.750 -0.6806 0.02805 0.02407 -0.0364 1.0000 0.0098 -7.500 -0.6613 0.02640 0.02232 -0.0359 1.0000 0.0100 -7.250 -0.6424 0.02492 0.02073 -0.0350 1.0000 0.0104 -7.000 -0.6240 0.02356 0.01925 -0.0338 1.0000 0.0108 -6.750 -0.5962 0.02214 0.01768 -0.0342 0.9985 0.0115 -6.500 -0.5598 0.02320 0.01857 -0.0357 0.9961 0.0130 -6.250 -0.5264 0.02196 0.01711 -0.0371 0.9940 0.0131 -6.000 -0.4948 0.02021 0.01520 -0.0382 0.9901 0.0131 -5.750 -0.4682 0.01377 0.00861 -0.0376 0.9862 0.0098 -5.500 -0.4368 0.01290 0.00774 -0.0387 0.9807 0.0103 -5.250 -0.4069 0.01220 0.00702 -0.0393 0.9730 0.0109 -5.000 -0.3786 0.01152 0.00630 -0.0395 0.9634 0.0114 -4.750 -0.3523 0.01090 0.00562 -0.0392 0.9518 0.0117 -4.500 -0.3269 0.01038 0.00503 -0.0387 0.9394 0.0121 -4.250 -0.3006 0.01011 0.00471 -0.0383 0.9275 0.0128 -4.000 -0.2743 0.00970 0.00422 -0.0380 0.9155 0.0133 -3.750 -0.2483 0.00893 0.00331 -0.0377 0.9025 0.0143 -3.500 -0.2212 0.00861 0.00290 -0.0375 0.8890 0.0155 -3.250 -0.1936 0.00837 0.00259 -0.0374 0.8754 0.0167 -3.000 -0.1660 0.00820 0.00232 -0.0372 0.8590 0.0182 -2.750 -0.1382 0.00804 0.00205 -0.0371 0.8408 0.0206 -2.500 -0.1102 0.00790 0.00184 -0.0370 0.8218 0.0262 -2.250 -0.0854 0.00589 0.00118 -0.0378 0.8010 0.4288 -2.000 -0.0571 0.00593 0.00120 -0.0378 0.7784 0.4646 -1.750 -0.0287 0.00603 0.00120 -0.0378 0.7536 0.4768 -1.500 -0.0004 0.00611 0.00121 -0.0379 0.7268 0.4857 -1.250 0.0282 0.00624 0.00121 -0.0379 0.7022 0.4931 -0.750 0.0854 0.00646 0.00127 -0.0382 0.6614 0.5065 -0.500 0.1140 0.00648 0.00124 -0.0383 0.6435 0.5098 -0.250 0.1427 0.00654 0.00124 -0.0385 0.6269 0.5126 0.000 0.1715 0.00660 0.00126 -0.0386 0.6126 0.5156 0.250 0.2003 0.00667 0.00127 -0.0388 0.5989 0.5185 0.500 0.2292 0.00674 0.00129 -0.0390 0.5836 0.5208 0.750 0.2578 0.00678 0.00128 -0.0392 0.5667 0.5231 1.000 0.2864 0.00683 0.00129 -0.0393 0.5479 0.5252 1.250 0.3150 0.00690 0.00132 -0.0395 0.5238 0.5273 1.500 0.3433 0.00703 0.00135 -0.0396 0.4957 0.5295 1.750 0.3717 0.00716 0.00140 -0.0398 0.4712 0.5318 2.000 0.4001 0.00729 0.00146 -0.0399 0.4525 0.5339 2.250 0.4286 0.00741 0.00153 -0.0401 0.4382 0.5357 2.500 0.4570 0.00747 0.00159 -0.0403 0.4256 0.5384 2.750 0.4854 0.00755 0.00167 -0.0404 0.4134 0.5410 3.000 0.5139 0.00765 0.00177 -0.0406 0.4026 0.5437 3.250 0.5423 0.00776 0.00186 -0.0407 0.3906 0.5464 3.500 0.5705 0.00790 0.00195 -0.0409 0.3676 0.5490 3.750 0.5981 0.00811 0.00205 -0.0409 0.3301 0.5517 4.000 0.6250 0.00844 0.00221 -0.0410 0.2799 0.5548 4.250 0.6520 0.00877 0.00242 -0.0410 0.2477 0.5581 4.500 0.6797 0.00898 0.00261 -0.0411 0.2325 0.5617 4.750 0.7073 0.00920 0.00280 -0.0411 0.2192 0.5652 5.000 0.7348 0.00939 0.00300 -0.0412 0.2052 0.5693 5.250 0.7623 0.00959 0.00319 -0.0412 0.1902 0.5737 5.500 0.7895 0.00984 0.00337 -0.0413 0.1669 0.5782 5.750 0.8149 0.01037 0.00370 -0.0411 0.1185 0.5833 6.000 0.8408 0.01080 0.00406 -0.0410 0.0942 0.5893 6.250 0.8664 0.01128 0.00443 -0.0409 0.0671 0.5957 6.500 0.8920 0.01173 0.00482 -0.0407 0.0492 0.6038 6.750 0.9181 0.01208 0.00519 -0.0406 0.0403 0.6136 7.000 0.9441 0.01242 0.00556 -0.0404 0.0317 0.6264 7.250 0.9690 0.01292 0.00606 -0.0401 0.0202 0.6442 7.500 0.9938 0.01338 0.00659 -0.0398 0.0152 0.6720 7.750 1.0188 0.01365 0.00712 -0.0395 0.0134 0.7373 8.000 1.0391 0.01355 0.00761 -0.0380 0.0121 1.0000 8.250 1.0620 0.01439 0.00851 -0.0373 0.0104 1.0000 8.500 1.0863 0.01494 0.00913 -0.0369 0.0099 1.0000 8.750 1.1105 0.01547 0.00971 -0.0365 0.0093 1.0000 9.000 1.1342 0.01603 0.01032 -0.0360 0.0086 1.0000 9.250 1.1573 0.01665 0.01098 -0.0355 0.0080 1.0000 9.500 1.1767 0.01770 0.01212 -0.0345 0.0074 1.0000 9.750 1.1930 0.01908 0.01366 -0.0331 0.0070 1.0000 10.000 1.2145 0.01976 0.01441 -0.0324 0.0068 1.0000 10.250 1.2343 0.02057 0.01531 -0.0315 0.0065 1.0000 10.500 1.2529 0.02149 0.01632 -0.0304 0.0063 1.0000 10.750 1.2702 0.02248 0.01740 -0.0293 0.0060 1.0000 11.000 1.2864 0.02349 0.01851 -0.0280 0.0058 1.0000 11.250 1.3014 0.02455 0.01966 -0.0266 0.0056 1.0000 11.500 1.3146 0.02566 0.02086 -0.0251 0.0054 1.0000 11.750 1.3242 0.02681 0.02210 -0.0231 0.0053 1.0000 12.000 1.3292 0.02816 0.02355 -0.0207 0.0052 1.0000 12.250 1.3302 0.02994 0.02545 -0.0183 0.0050 1.0000 12.500 1.3265 0.03233 0.02798 -0.0162 0.0049 1.0000 12.750 1.3146 0.03580 0.03166 -0.0144 0.0048 1.0000 13.250 1.2935 0.04363 0.03988 -0.0137 0.0046 1.0000 13.500 1.2965 0.04635 0.04273 -0.0145 0.0045 1.0000 13.750 1.2948 0.04987 0.04638 -0.0158 0.0045 1.0000 14.000 1.2899 0.05403 0.05068 -0.0174 0.0044 1.0000 14.250 1.2819 0.05876 0.05555 -0.0195 0.0044 1.0000 14.500 1.2728 0.06388 0.06081 -0.0219 0.0044 1.0000 14.750 1.2600 0.06971 0.06679 -0.0247 0.0043 1.0000 15.000 1.2448 0.07616 0.07338 -0.0279 0.0043 1.0000 15.250 1.2271 0.08324 0.08060 -0.0315 0.0043 1.0000 15.500 1.2078 0.09084 0.08834 -0.0354 0.0043 1.0000 15.750 1.1878 0.09889 0.09653 -0.0396 0.0043 1.0000 16.000 1.1657 0.10767 0.10544 -0.0441 0.0043 1.0000 16.250 1.1440 0.11674 0.11464 -0.0489 0.0044 1.0000 16.500 1.1184 0.12695 0.12499 -0.0543 0.0044 1.0000 16.750 1.0945 0.13715 0.13530 -0.0597 0.0045 1.0000 17.000 1.0640 0.14949 0.14778 -0.0664 0.0045 1.0000