XFOIL Version 6.96 Calculated polar for: SD7084 (9.6%) 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.4356 0.10188 0.09957 -0.0269 1.0000 0.0190 -10.000 -0.4339 0.09773 0.09544 -0.0287 1.0000 0.0191 -9.750 -0.4475 0.09051 0.08827 -0.0314 1.0000 0.0196 -9.500 -0.4439 0.08801 0.08579 -0.0316 1.0000 0.0201 -9.250 -0.4385 0.08583 0.08362 -0.0319 1.0000 0.0207 -9.000 -0.4354 0.08309 0.08090 -0.0328 1.0000 0.0214 -8.750 -0.4373 0.07927 0.07712 -0.0346 1.0000 0.0217 -8.500 -0.4420 0.07529 0.07318 -0.0365 1.0000 0.0221 -8.250 -0.4535 0.07124 0.06919 -0.0383 1.0000 0.0223 -8.000 -0.4785 0.06778 0.06579 -0.0384 1.0000 0.0222 -7.750 -0.5022 0.06379 0.06180 -0.0378 1.0000 0.0217 -7.500 -0.5116 0.05925 0.05719 -0.0388 0.9992 0.0220 -7.250 -0.4917 0.05176 0.04949 -0.0466 0.9950 0.0234 -7.000 -0.4645 0.04585 0.04305 -0.0516 0.9901 0.0263 -6.750 -0.4578 0.03517 0.03175 -0.0561 0.9849 0.0276 -6.500 -0.4446 0.02487 0.02041 -0.0557 0.9795 0.0198 -6.250 -0.4175 0.02186 0.01701 -0.0565 0.9760 0.0199 -6.000 -0.3858 0.01998 0.01494 -0.0581 0.9737 0.0209 -5.750 -0.3519 0.01778 0.01244 -0.0595 0.9721 0.0212 -5.500 -0.3166 0.01626 0.01071 -0.0612 0.9708 0.0217 -5.250 -0.2899 0.01517 0.00948 -0.0609 0.9657 0.0222 -5.000 -0.2583 0.01419 0.00839 -0.0617 0.9621 0.0231 -4.750 -0.2256 0.01345 0.00758 -0.0626 0.9591 0.0245 -4.500 -0.1969 0.01270 0.00673 -0.0626 0.9548 0.0253 -4.250 -0.1715 0.01211 0.00608 -0.0619 0.9486 0.0261 -4.000 -0.1446 0.01138 0.00526 -0.0615 0.9441 0.0269 -3.750 -0.1226 0.01067 0.00449 -0.0602 0.9369 0.0288 -3.500 -0.0972 0.01026 0.00405 -0.0594 0.9310 0.0314 -3.250 -0.0726 0.00997 0.00372 -0.0585 0.9242 0.0349 -3.000 -0.0482 0.00952 0.00325 -0.0574 0.9173 0.0433 -2.750 -0.0250 0.00892 0.00288 -0.0564 0.9099 0.1009 -2.500 -0.0013 0.00840 0.00264 -0.0555 0.9025 0.1798 -2.250 0.0221 0.00790 0.00245 -0.0546 0.8939 0.2761 -2.000 0.0454 0.00735 0.00227 -0.0537 0.8862 0.3928 -1.750 0.0680 0.00685 0.00216 -0.0526 0.8756 0.5102 -1.500 0.0901 0.00639 0.00207 -0.0513 0.8653 0.6272 -1.250 0.1121 0.00601 0.00201 -0.0496 0.8547 0.7310 -1.000 0.1354 0.00577 0.00195 -0.0482 0.8433 0.8007 -0.750 0.1597 0.00559 0.00191 -0.0469 0.8301 0.8641 -0.500 0.1927 0.00551 0.00189 -0.0473 0.8164 0.9275 -0.250 0.2347 0.00554 0.00185 -0.0500 0.8013 0.9566 0.000 0.2758 0.00560 0.00181 -0.0525 0.7831 0.9725 0.250 0.3161 0.00567 0.00176 -0.0550 0.7624 0.9842 0.500 0.3592 0.00576 0.00171 -0.0582 0.7397 0.9930 0.750 0.4028 0.00585 0.00165 -0.0616 0.7145 0.9999 1.000 0.4259 0.00594 0.00161 -0.0606 0.6898 1.0000 1.250 0.4487 0.00605 0.00160 -0.0596 0.6654 1.0000 1.500 0.4716 0.00619 0.00161 -0.0586 0.6406 1.0000 1.750 0.4947 0.00634 0.00164 -0.0576 0.6157 1.0000 2.000 0.5181 0.00650 0.00168 -0.0567 0.5909 1.0000 2.250 0.5415 0.00667 0.00174 -0.0558 0.5666 1.0000 2.500 0.5649 0.00686 0.00182 -0.0549 0.5421 1.0000 2.750 0.5885 0.00705 0.00191 -0.0541 0.5176 1.0000 3.000 0.6121 0.00725 0.00201 -0.0532 0.4939 1.0000 3.250 0.6356 0.00747 0.00212 -0.0524 0.4705 1.0000 3.500 0.6593 0.00769 0.00225 -0.0516 0.4471 1.0000 3.750 0.6830 0.00791 0.00240 -0.0508 0.4253 1.0000 4.000 0.7066 0.00815 0.00255 -0.0500 0.4030 1.0000 4.250 0.7303 0.00839 0.00271 -0.0492 0.3824 1.0000 4.500 0.7540 0.00864 0.00289 -0.0485 0.3622 1.0000 5.000 0.8015 0.00916 0.00329 -0.0470 0.3254 1.0000 5.250 0.8255 0.00942 0.00350 -0.0463 0.3082 1.0000 5.500 0.8494 0.00968 0.00372 -0.0456 0.2923 1.0000 5.750 0.8732 0.00996 0.00398 -0.0449 0.2769 1.0000 6.000 0.8971 0.01025 0.00423 -0.0443 0.2621 1.0000 6.250 0.9209 0.01053 0.00449 -0.0436 0.2479 1.0000 6.500 0.9447 0.01083 0.00476 -0.0429 0.2337 1.0000 6.750 0.9681 0.01116 0.00504 -0.0422 0.2174 1.0000 7.000 0.9914 0.01150 0.00535 -0.0416 0.1988 1.0000 7.250 1.0141 0.01189 0.00565 -0.0408 0.1771 1.0000 7.500 1.0367 0.01230 0.00600 -0.0400 0.1581 1.0000 7.750 1.0589 0.01274 0.00638 -0.0392 0.1382 1.0000 8.000 1.0801 0.01327 0.00683 -0.0383 0.1158 1.0000 8.250 1.0999 0.01392 0.00735 -0.0372 0.0902 1.0000 8.500 1.1172 0.01481 0.00803 -0.0358 0.0590 1.0000 8.750 1.1290 0.01623 0.00916 -0.0336 0.0224 1.0000 9.000 1.1437 0.01735 0.01029 -0.0315 0.0146 1.0000 9.250 1.1607 0.01818 0.01123 -0.0299 0.0127 1.0000 9.500 1.1772 0.01898 0.01212 -0.0282 0.0117 1.0000 9.750 1.1912 0.01993 0.01316 -0.0263 0.0107 1.0000 10.000 1.1971 0.02137 0.01473 -0.0232 0.0098 1.0000 10.250 1.2059 0.02231 0.01577 -0.0204 0.0095 1.0000 10.500 1.2150 0.02320 0.01675 -0.0178 0.0092 1.0000 10.750 1.2217 0.02427 0.01793 -0.0150 0.0089 1.0000 11.000 1.2277 0.02544 0.01920 -0.0124 0.0086 1.0000 11.250 1.2317 0.02681 0.02068 -0.0098 0.0085 1.0000 11.500 1.2359 0.02824 0.02222 -0.0074 0.0083 1.0000 11.750 1.2383 0.02989 0.02398 -0.0052 0.0081 1.0000 12.000 1.2414 0.03156 0.02575 -0.0034 0.0078 1.0000 12.250 1.2425 0.03351 0.02783 -0.0017 0.0076 1.0000 12.500 1.2430 0.03563 0.03006 -0.0003 0.0075 1.0000 12.750 1.2420 0.03808 0.03265 0.0010 0.0075 1.0000 13.000 1.2403 0.04073 0.03541 0.0018 0.0074 1.0000 13.250 1.2380 0.04356 0.03834 0.0023 0.0072 1.0000 13.500 1.2337 0.04680 0.04171 0.0025 0.0071 1.0000 13.750 1.2268 0.05058 0.04563 0.0025 0.0069 1.0000 14.000 1.2257 0.05373 0.04893 0.0020 0.0070 1.0000 14.250 1.2186 0.05783 0.05318 0.0013 0.0070 1.0000 14.500 1.2103 0.06228 0.05778 0.0002 0.0069 1.0000 14.750 1.1959 0.06785 0.06355 -0.0014 0.0068 1.0000 15.000 1.1927 0.07193 0.06776 -0.0033 0.0069 1.0000 15.250 1.1810 0.07753 0.07352 -0.0057 0.0069 1.0000 15.500 1.1662 0.08391 0.08007 -0.0087 0.0069 1.0000 15.750 1.1592 0.08929 0.08560 -0.0118 0.0070 1.0000 16.000 1.1483 0.09559 0.09206 -0.0153 0.0070 1.0000 16.250 1.1339 0.10274 0.09937 -0.0193 0.0070 1.0000 16.500 1.1194 0.11031 0.10711 -0.0238 0.0071 1.0000 16.750 1.1030 0.11863 0.11560 -0.0287 0.0072 1.0000 17.000 1.0828 0.12815 0.12531 -0.0344 0.0073 1.0000 17.250 1.0642 0.13771 0.13502 -0.0402 0.0073 1.0000 17.500 1.0218 0.15477 0.15237 -0.0505 0.0078 1.0000