XFOIL Version 6.96 Calculated polar for: NREL's S820 Airfoil 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.4184 0.11775 0.11138 -0.0553 1.0000 0.0454 -11.000 -0.4273 0.11543 0.10913 -0.0533 1.0000 0.0442 -10.750 -0.4310 0.11144 0.10518 -0.0546 0.9979 0.0429 -10.500 -0.4301 0.10519 0.09894 -0.0596 0.9931 0.0411 -10.250 -0.4374 0.09799 0.09172 -0.0655 0.9878 0.0393 -10.000 -0.4546 0.09093 0.08457 -0.0717 0.9818 0.0379 -9.750 -0.4879 0.08517 0.07856 -0.0764 0.9736 0.0365 -9.500 -0.5081 0.08257 0.07569 -0.0769 0.9654 0.0357 -9.250 -0.5075 0.07881 0.07188 -0.0775 0.9604 0.0351 -9.000 -0.5166 0.07618 0.06915 -0.0763 0.9537 0.0348 -8.750 -0.5231 0.07301 0.06582 -0.0756 0.9474 0.0344 -8.500 -0.5294 0.07001 0.06263 -0.0742 0.9413 0.0340 -8.250 -0.5347 0.06735 0.05977 -0.0723 0.9350 0.0336 -8.000 -0.5321 0.06418 0.05630 -0.0716 0.9307 0.0331 -7.750 -0.5381 0.06202 0.05391 -0.0683 0.9243 0.0328 -7.500 -0.5344 0.05936 0.05094 -0.0666 0.9195 0.0323 -7.250 -0.5235 0.05636 0.04753 -0.0658 0.9161 0.0320 -7.000 -0.5236 0.05447 0.04538 -0.0623 0.9105 0.0317 -6.750 -0.5126 0.05218 0.04273 -0.0606 0.9064 0.0315 -6.500 -0.4936 0.04976 0.03987 -0.0599 0.9033 0.0313 -6.250 -0.4746 0.04755 0.03727 -0.0588 0.9002 0.0314 -6.000 -0.4621 0.04597 0.03541 -0.0564 0.8959 0.0315 -5.750 -0.4396 0.04429 0.03343 -0.0555 0.8929 0.0318 -5.500 -0.4105 0.04274 0.03156 -0.0553 0.8906 0.0337 -5.250 -0.3761 0.04164 0.03012 -0.0557 0.8886 0.0357 -5.000 -0.3346 0.04027 0.02878 -0.0569 0.8876 0.0390 -4.750 -0.3193 0.03975 0.02816 -0.0544 0.8838 0.0406 -4.500 -0.3062 0.03916 0.02745 -0.0517 0.8800 0.0425 -4.250 -0.2911 0.03852 0.02659 -0.0497 0.8767 0.0464 -4.000 -0.2761 0.03758 0.02563 -0.0483 0.8738 0.0515 -3.750 -0.2715 0.03700 0.02492 -0.0450 0.8694 0.0575 -3.500 -0.2659 0.03627 0.02415 -0.0420 0.8651 0.0652 -3.250 -0.2549 0.03518 0.02313 -0.0401 0.8618 0.0886 -3.000 -0.2674 0.03262 0.02369 -0.0332 0.8588 0.5862 -2.750 -0.2748 0.03453 0.02559 -0.0234 0.8537 0.7005 -2.500 -0.2575 0.03950 0.03060 -0.0088 0.8515 0.8069 -2.250 -0.2466 0.03921 0.03002 -0.0068 0.8480 0.8146 -2.000 -0.2203 0.03910 0.02957 -0.0073 0.8453 0.8181 -1.750 -0.2026 0.03893 0.02913 -0.0065 0.8421 0.8227 -1.500 -0.2015 0.03863 0.02867 -0.0032 0.8373 0.8288 -1.250 -0.1801 0.03859 0.02841 -0.0030 0.8340 0.8322 -1.000 -0.1560 0.03854 0.02815 -0.0033 0.8310 0.8362 -0.750 -0.1361 0.03845 0.02786 -0.0031 0.8280 0.8409 -0.500 -0.1271 0.03841 0.02769 -0.0010 0.8233 0.8454 -0.250 -0.1071 0.03845 0.02759 -0.0007 0.8195 0.8495 0.000 -0.0831 0.03848 0.02746 -0.0011 0.8164 0.8539 0.250 -0.0622 0.03854 0.02739 -0.0010 0.8130 0.8583 0.500 -0.0496 0.03866 0.02742 0.0005 0.8080 0.8628 0.750 -0.0278 0.03878 0.02745 0.0005 0.8040 0.8677 1.000 -0.0010 0.03893 0.02749 -0.0003 0.8009 0.8723 1.250 0.0155 0.03914 0.02766 0.0005 0.7959 0.8767 1.500 0.0342 0.03935 0.02780 0.0010 0.7911 0.8821 1.750 0.0615 0.03957 0.02796 0.0001 0.7872 0.8873 2.000 0.0845 0.03987 0.02824 -0.0001 0.7828 0.8922 2.250 0.1012 0.04013 0.02849 0.0005 0.7768 0.8983 2.500 0.1305 0.04044 0.02878 -0.0007 0.7728 0.9034 2.750 0.1530 0.04080 0.02915 -0.0009 0.7674 0.9095 3.000 0.1743 0.04115 0.02953 -0.0011 0.7613 0.9165 3.250 0.2092 0.04152 0.02993 -0.0032 0.7572 0.9220 3.500 0.2269 0.04195 0.03042 -0.0030 0.7498 0.9300 3.750 0.2608 0.04238 0.03091 -0.0051 0.7444 0.9361 4.000 0.2888 0.04285 0.03147 -0.0065 0.7380 0.9442 4.250 0.3206 0.04334 0.03205 -0.0086 0.7310 0.9517 4.500 0.3567 0.04378 0.03259 -0.0112 0.7250 0.9597 4.750 0.3866 0.04429 0.03323 -0.0132 0.7165 0.9696 5.000 0.4198 0.04472 0.03382 -0.0156 0.7087 0.9817 5.500 0.4612 0.04521 0.03448 -0.0158 0.6903 1.0000 5.750 0.4968 0.04511 0.03453 -0.0173 0.6844 1.0000 6.000 0.5113 0.04545 0.03495 -0.0165 0.6724 1.0000 6.250 0.5308 0.04573 0.03533 -0.0162 0.6608 1.0000 6.750 0.5839 0.04573 0.03564 -0.0168 0.6388 1.0000 7.000 0.6178 0.04524 0.03533 -0.0174 0.6284 1.0000 7.250 0.6415 0.04509 0.03534 -0.0171 0.6145 1.0000 7.500 0.6666 0.04475 0.03518 -0.0167 0.6001 1.0000 7.750 0.6856 0.04467 0.03530 -0.0157 0.5830 1.0000 8.000 0.7033 0.04463 0.03544 -0.0146 0.5638 1.0000 8.500 0.7510 0.04334 0.03457 -0.0126 0.5253 1.0000 8.750 0.7733 0.04270 0.03416 -0.0113 0.5022 1.0000 9.000 0.7976 0.04192 0.03356 -0.0099 0.4741 1.0000 9.250 0.8287 0.04056 0.03231 -0.0087 0.4385 1.0000 9.500 0.8605 0.03932 0.03098 -0.0073 0.3901 1.0000 9.750 0.8807 0.03939 0.03074 -0.0057 0.3394 1.0000 10.000 0.8903 0.04057 0.03167 -0.0040 0.2981 1.0000 10.250 0.8972 0.04214 0.03304 -0.0025 0.2636 1.0000 10.500 0.9046 0.04381 0.03456 -0.0012 0.2356 1.0000 10.750 0.9120 0.04554 0.03616 0.0000 0.2116 1.0000 11.000 0.9217 0.04724 0.03782 0.0010 0.1905 1.0000 11.250 0.9321 0.04894 0.03954 0.0018 0.1722 1.0000 11.500 0.9431 0.05064 0.04121 0.0026 0.1561 1.0000 11.750 0.9554 0.05233 0.04292 0.0033 0.1415 1.0000 12.000 0.9671 0.05410 0.04474 0.0040 0.1279 1.0000 12.250 0.9804 0.05589 0.04665 0.0045 0.1155 1.0000 12.500 0.9912 0.05789 0.04879 0.0051 0.1040 1.0000 12.750 1.0031 0.05994 0.05100 0.0057 0.0938 1.0000 13.000 1.0125 0.06214 0.05325 0.0062 0.0850 1.0000 13.250 1.0207 0.06459 0.05591 0.0066 0.0773 1.0000 13.500 1.0270 0.06736 0.05894 0.0071 0.0705 1.0000 13.750 1.0305 0.07021 0.06197 0.0074 0.0650 1.0000 14.000 1.0332 0.07341 0.06533 0.0077 0.0603 1.0000 14.250 1.0281 0.07739 0.06967 0.0077 0.0564 1.0000 14.500 1.0262 0.08091 0.07334 0.0075 0.0533 1.0000 14.750 1.0254 0.08452 0.07700 0.0072 0.0505 1.0000 15.000 1.0114 0.08999 0.08286 0.0062 0.0492 1.0000 15.250 0.9935 0.09619 0.08940 0.0043 0.0480 1.0000 15.500 0.9751 0.10291 0.09639 0.0018 0.0476 1.0000 15.750 0.9530 0.11066 0.10437 -0.0018 0.0475 1.0000 16.000 0.9291 0.11959 0.11349 -0.0066 0.0482 1.0000 16.250 0.9044 0.12963 0.12366 -0.0124 0.0490 1.0000