XFOIL Version 6.96 Calculated polar for: GOE 523 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 0.0820 0.03976 0.03658 -0.2175 0.8462 0.0233 -11.250 0.0452 0.03425 0.03094 -0.2194 0.8364 0.0233 -11.000 0.0243 0.03053 0.02709 -0.2206 0.8281 0.0233 -10.750 0.0197 0.02675 0.02319 -0.2248 0.8205 0.0233 -10.500 0.0310 0.02369 0.01996 -0.2300 0.8136 0.0234 -10.250 0.0539 0.02132 0.01746 -0.2355 0.8078 0.0235 -10.000 0.0844 0.01894 0.01490 -0.2422 0.8016 0.0236 -9.750 0.1190 0.01716 0.01296 -0.2480 0.7956 0.0239 -9.500 0.1536 0.01598 0.01167 -0.2520 0.7882 0.0241 -9.250 0.1842 0.01523 0.01079 -0.2542 0.7781 0.0242 -9.000 0.2143 0.01463 0.01010 -0.2558 0.7665 0.0244 -8.750 0.2435 0.01414 0.00949 -0.2570 0.7549 0.0246 -8.500 0.2719 0.01371 0.00895 -0.2579 0.7423 0.0248 -8.250 0.3006 0.01334 0.00847 -0.2587 0.7292 0.0250 -8.000 0.3285 0.01302 0.00804 -0.2592 0.7153 0.0252 -7.750 0.3552 0.01277 0.00767 -0.2594 0.6992 0.0255 -7.500 0.3814 0.01255 0.00731 -0.2595 0.6825 0.0258 -7.250 0.4081 0.01232 0.00695 -0.2597 0.6678 0.0260 -7.000 0.4350 0.01212 0.00663 -0.2598 0.6554 0.0262 -6.750 0.4634 0.01190 0.00632 -0.2602 0.6449 0.0264 -6.500 0.4908 0.01173 0.00605 -0.2603 0.6353 0.0266 -6.250 0.5193 0.01156 0.00580 -0.2607 0.6266 0.0268 -6.000 0.5467 0.01143 0.00558 -0.2608 0.6189 0.0270 -5.750 0.5760 0.01127 0.00536 -0.2612 0.6133 0.0272 -5.500 0.6044 0.01113 0.00517 -0.2614 0.6070 0.0273 -5.250 0.6331 0.01094 0.00490 -0.2619 0.6006 0.0277 -5.000 0.6627 0.01077 0.00469 -0.2624 0.5952 0.0281 -4.750 0.6905 0.01066 0.00454 -0.2625 0.5890 0.0285 -4.500 0.7166 0.01061 0.00443 -0.2622 0.5833 0.0288 -4.250 0.7444 0.01052 0.00432 -0.2622 0.5788 0.0292 -4.000 0.7719 0.01045 0.00422 -0.2622 0.5737 0.0297 -3.750 0.7980 0.01043 0.00414 -0.2619 0.5675 0.0301 -3.500 0.8238 0.01042 0.00409 -0.2616 0.5617 0.0307 -3.250 0.8507 0.01040 0.00403 -0.2614 0.5557 0.0312 -3.000 0.8765 0.01041 0.00399 -0.2610 0.5493 0.0316 -2.750 0.9025 0.01041 0.00395 -0.2607 0.5435 0.0324 -2.500 0.9293 0.01041 0.00393 -0.2606 0.5370 0.0332 -2.250 0.9540 0.01048 0.00395 -0.2600 0.5289 0.0340 -2.000 0.9797 0.01054 0.00397 -0.2597 0.5218 0.0351 -1.750 1.0047 0.01063 0.00401 -0.2591 0.5137 0.0361 -1.500 1.0294 0.01073 0.00407 -0.2586 0.5061 0.0382 -1.250 1.0539 0.01084 0.00415 -0.2580 0.4968 0.0409 -1.000 1.0780 0.01097 0.00424 -0.2574 0.4878 0.0473 -0.750 1.1029 0.01107 0.00435 -0.2570 0.4785 0.0643 -0.500 1.1274 0.01118 0.00447 -0.2565 0.4705 0.0868 -0.250 1.1517 0.01130 0.00463 -0.2560 0.4617 0.1176 0.000 1.1748 0.01148 0.00479 -0.2552 0.4538 0.1349 0.250 1.1982 0.01166 0.00495 -0.2545 0.4459 0.1463 0.500 1.2206 0.01189 0.00514 -0.2536 0.4380 0.1594 0.750 1.2448 0.01203 0.00532 -0.2531 0.4306 0.1863 1.000 1.2675 0.01222 0.00559 -0.2525 0.4221 0.2500 1.250 1.2912 0.01238 0.00580 -0.2519 0.4161 0.2854 1.500 1.3142 0.01259 0.00602 -0.2512 0.4101 0.3094 1.750 1.3363 0.01285 0.00627 -0.2503 0.4045 0.3296 2.000 1.3597 0.01304 0.00649 -0.2496 0.4004 0.3487 2.250 1.3828 0.01324 0.00672 -0.2490 0.3966 0.3683 2.750 1.4270 0.01375 0.00727 -0.2473 0.3882 0.4177 3.000 1.4491 0.01402 0.00756 -0.2465 0.3844 0.4413 3.250 1.4721 0.01425 0.00782 -0.2458 0.3809 0.4583 3.500 1.4936 0.01453 0.00811 -0.2449 0.3768 0.4723 3.750 1.5140 0.01488 0.00846 -0.2438 0.3722 0.4850 4.000 1.5340 0.01526 0.00883 -0.2426 0.3676 0.4969 4.250 1.5562 0.01554 0.00913 -0.2419 0.3648 0.5111 4.500 1.5779 0.01584 0.00946 -0.2410 0.3614 0.5238 4.750 1.5981 0.01621 0.00983 -0.2400 0.3576 0.5321 5.000 1.6172 0.01664 0.01026 -0.2388 0.3536 0.5393 5.250 1.6368 0.01706 0.01068 -0.2376 0.3498 0.5482 5.500 1.6575 0.01743 0.01106 -0.2367 0.3454 0.5557 5.750 1.6768 0.01787 0.01151 -0.2356 0.3407 0.5619 6.000 1.6933 0.01847 0.01208 -0.2341 0.3348 0.5681 6.250 1.7125 0.01893 0.01254 -0.2330 0.3301 0.5735 6.500 1.7314 0.01941 0.01304 -0.2319 0.3251 0.5789 6.750 1.7479 0.02004 0.01366 -0.2305 0.3196 0.5839 7.000 1.7652 0.02063 0.01424 -0.2292 0.3154 0.5889 7.250 1.7835 0.02116 0.01480 -0.2281 0.3110 0.5952 7.500 1.8004 0.02180 0.01544 -0.2268 0.3058 0.6032 7.750 1.8149 0.02258 0.01621 -0.2252 0.3009 0.6092 8.000 1.8327 0.02317 0.01684 -0.2241 0.2974 0.6151 8.250 1.8497 0.02384 0.01752 -0.2229 0.2930 0.6214 8.500 1.8637 0.02470 0.01838 -0.2214 0.2878 0.6271 8.750 1.8783 0.02553 0.01922 -0.2200 0.2831 0.6313 9.000 1.8943 0.02630 0.02002 -0.2188 0.2783 0.6355 9.250 1.9072 0.02728 0.02100 -0.2172 0.2729 0.6397 9.500 1.9195 0.02834 0.02205 -0.2156 0.2670 0.6438 9.750 1.9322 0.02940 0.02310 -0.2142 0.2599 0.6479 10.000 1.9411 0.03075 0.02445 -0.2123 0.2529 0.6524 10.250 1.9552 0.03174 0.02547 -0.2111 0.2484 0.6572 10.500 1.9653 0.03306 0.02679 -0.2095 0.2424 0.6615 10.750 1.9745 0.03449 0.02822 -0.2078 0.2363 0.6654 11.000 1.9858 0.03577 0.02953 -0.2065 0.2308 0.6699 11.250 1.9945 0.03731 0.03108 -0.2049 0.2258 0.6750 11.500 2.0041 0.03879 0.03258 -0.2035 0.2211 0.6801 11.750 2.0137 0.04031 0.03413 -0.2022 0.2164 0.6853 12.000 2.0205 0.04211 0.03595 -0.2006 0.2104 0.6908 12.250 2.0269 0.04401 0.03787 -0.1992 0.2052 0.6961 12.500 2.0336 0.04590 0.03978 -0.1978 0.1987 0.7017 12.750 2.0362 0.04827 0.04217 -0.1963 0.1923 0.7083 13.250 2.0403 0.05332 0.04725 -0.1934 0.1758 0.7250 13.500 2.0348 0.05681 0.05072 -0.1918 0.1633 0.7350 13.750 2.0026 0.06366 0.05743 -0.1891 0.1324 0.7414 14.000 1.9674 0.07133 0.06501 -0.1869 0.1040 0.7467 14.250 1.9479 0.07732 0.07100 -0.1859 0.0892 0.7612 14.500 1.9395 0.08150 0.07542 -0.1850 0.0825 0.9353 14.750 1.9338 0.08567 0.07964 -0.1845 0.0780 1.0000 15.000 1.9295 0.08978 0.08380 -0.1842 0.0742 1.0000 15.250 1.9285 0.09344 0.08753 -0.1841 0.0717 1.0000 15.500 1.9256 0.09740 0.09155 -0.1840 0.0684 1.0000 15.750 1.9190 0.10197 0.09617 -0.1841 0.0648 1.0000 16.000 1.9158 0.10603 0.10028 -0.1842 0.0612 1.0000 16.250 1.9077 0.11088 0.10516 -0.1846 0.0561 1.0000 16.500 1.8928 0.11687 0.11115 -0.1852 0.0460 1.0000 16.750 1.8651 0.12502 0.11929 -0.1865 0.0306 1.0000