XFOIL Version 6.96 Calculated polar for: GOE 506 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 ------ -------- --------- --------- -------- -------- -------- -16.250 -0.5535 0.08664 0.08444 -0.0959 0.9905 0.0120 -16.000 -0.5812 0.07682 0.07446 -0.1032 0.9884 0.0122 -15.750 -0.6083 0.06773 0.06519 -0.1105 0.9863 0.0122 -15.500 -0.6318 0.05934 0.05661 -0.1177 0.9843 0.0121 -15.250 -0.6521 0.05214 0.04924 -0.1235 0.9799 0.0121 -15.000 -0.6494 0.04784 0.04484 -0.1280 0.9759 0.0122 -14.750 -0.6482 0.04282 0.03967 -0.1338 0.9728 0.0125 -14.500 -0.6438 0.03832 0.03502 -0.1393 0.9688 0.0127 -14.250 -0.6380 0.03418 0.03071 -0.1445 0.9631 0.0128 -14.000 -0.6185 0.03146 0.02784 -0.1495 0.9597 0.0131 -13.750 -0.6005 0.02862 0.02483 -0.1545 0.9556 0.0132 -13.500 -0.5860 0.02546 0.02146 -0.1593 0.9499 0.0134 -13.250 -0.5621 0.02347 0.01935 -0.1633 0.9454 0.0138 -13.000 -0.5358 0.02243 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0.00962 0.00348 -0.0540 0.3308 0.6471 2.000 0.4867 0.00947 0.00366 -0.0501 0.3263 0.7552 2.250 0.6395 0.00944 0.00407 -0.0777 0.3167 0.9536 2.500 0.6871 0.00977 0.00433 -0.0823 0.3116 0.9793 2.750 0.7230 0.00997 0.00451 -0.0843 0.3090 0.9902 3.000 0.7611 0.01019 0.00470 -0.0867 0.3066 0.9966 3.250 0.8034 0.01039 0.00486 -0.0902 0.3034 0.9995 3.500 0.8264 0.01056 0.00500 -0.0895 0.3007 1.0000 3.750 0.8408 0.01072 0.00515 -0.0870 0.2984 1.0000 4.000 0.8551 0.01092 0.00532 -0.0845 0.2954 1.0000 4.250 0.8725 0.01107 0.00546 -0.0826 0.2936 1.0000 4.500 0.8907 0.01121 0.00561 -0.0809 0.2921 1.0000 4.750 0.9092 0.01137 0.00577 -0.0792 0.2900 1.0000 5.000 0.9275 0.01154 0.00594 -0.0776 0.2871 1.0000 5.250 0.9454 0.01175 0.00613 -0.0759 0.2846 1.0000 5.500 0.9631 0.01198 0.00635 -0.0742 0.2819 1.0000 5.750 0.9810 0.01224 0.00658 -0.0726 0.2786 1.0000 6.000 1.0015 0.01241 0.00677 -0.0715 0.2769 1.0000 6.250 1.0218 0.01260 0.00697 -0.0703 0.2731 1.0000 6.500 1.0411 0.01284 0.00720 -0.0690 0.2686 1.0000 6.750 1.0594 0.01314 0.00747 -0.0676 0.2632 1.0000 7.000 1.0800 0.01336 0.00771 -0.0666 0.2598 1.0000 7.250 1.0983 0.01369 0.00798 -0.0653 0.2508 1.0000 7.500 1.1171 0.01402 0.00828 -0.0640 0.2398 1.0000 8.000 1.1317 0.01581 0.00963 -0.0583 0.1732 1.0000 8.250 1.1473 0.01634 0.01013 -0.0568 0.1664 1.0000 8.500 1.1641 0.01683 0.01061 -0.0554 0.1627 1.0000 8.750 1.1814 0.01730 0.01108 -0.0542 0.1603 1.0000 9.000 1.1979 0.01782 0.01159 -0.0528 0.1570 1.0000 9.250 1.2141 0.01837 0.01214 -0.0515 0.1535 1.0000 9.500 1.2332 0.01877 0.01257 -0.0506 0.1520 1.0000 9.750 1.2521 0.01918 0.01302 -0.0497 0.1502 1.0000 10.000 1.2693 0.01969 0.01355 -0.0486 0.1478 1.0000 10.250 1.2855 0.02028 0.01413 -0.0474 0.1447 1.0000 10.500 1.3000 0.02096 0.01481 -0.0461 0.1404 1.0000 10.750 1.3183 0.02143 0.01532 -0.0452 0.1378 1.0000 11.000 1.3350 0.02200 0.01587 -0.0442 0.1305 1.0000 11.250 1.3487 0.02277 0.01658 -0.0429 0.1181 1.0000 11.500 1.3327 0.02542 0.01888 -0.0383 0.0653 1.0000 11.750 1.3127 0.02852 0.02177 -0.0337 0.0215 1.0000 12.000 1.3200 0.02986 0.02313 -0.0320 0.0180 1.0000 12.250 1.3301 0.03103 0.02436 -0.0307 0.0168 1.0000 12.500 1.3382 0.03238 0.02574 -0.0294 0.0156 1.0000 12.750 1.3436 0.03399 0.02741 -0.0278 0.0143 1.0000 13.000 1.3527 0.03534 0.02881 -0.0267 0.0140 1.0000 13.250 1.3602 0.03685 0.03038 -0.0256 0.0134 1.0000 13.500 1.3664 0.03850 0.03209 -0.0244 0.0129 1.0000 13.750 1.3716 0.04029 0.03394 -0.0233 0.0124 1.0000 14.000 1.3740 0.04239 0.03611 -0.0222 0.0121 1.0000 14.250 1.3720 0.04497 0.03878 -0.0210 0.0116 1.0000 14.500 1.3721 0.04742 0.04131 -0.0200 0.0113 1.0000 14.750 1.3751 0.04966 0.04363 -0.0193 0.0112 1.0000 15.000 1.3760 0.05220 0.04625 -0.0187 0.0109 1.0000 15.250 1.3744 0.05510 0.04924 -0.0182 0.0107 1.0000 15.500 1.3732 0.05805 0.05227 -0.0180 0.0105 1.0000 15.750 1.3686 0.06149 0.05580 -0.0178 0.0102 1.0000 16.000 1.3652 0.06493 0.05933 -0.0179 0.0101 1.0000 16.250 1.3571 0.06908 0.06359 -0.0182 0.0099 1.0000 16.500 1.3506 0.07311 0.06770 -0.0187 0.0097 1.0000 16.750 1.3388 0.07790 0.07260 -0.0194 0.0096 1.0000 17.000 1.3248 0.08308 0.07790 -0.0203 0.0095 1.0000 17.250 1.3103 0.08842 0.08334 -0.0213 0.0094 1.0000 17.500 1.2932 0.09418 0.08923 -0.0226 0.0093 1.0000 17.750 1.2785 0.09963 0.09478 -0.0238 0.0092 1.0000 18.000 1.2630 0.10534 0.10060 -0.0253 0.0092 1.0000