XFOIL Version 6.94 Calculated polar for: SD7080 (9.2%) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3059 0.00567 0.00191 -0.0630 0.8101 0.9609 0.500 0.3909 0.00569 0.00168 -0.0688 0.7686 1.0000 1.000 0.4374 0.00591 0.00162 -0.0666 0.7196 1.0000 1.500 0.4861 0.00621 0.00165 -0.0650 0.6693 1.0000 2.000 0.5361 0.00656 0.00175 -0.0636 0.6176 1.0000 2.500 0.5867 0.00696 0.00190 -0.0625 0.5656 1.0000 3.000 0.6376 0.00739 0.00212 -0.0614 0.5147 1.0000 3.500 0.6885 0.00786 0.00238 -0.0605 0.4643 1.0000 4.000 0.7396 0.00836 0.00269 -0.0596 0.4165 1.0000 4.500 0.7904 0.00891 0.00308 -0.0587 0.3705 1.0000 5.000 0.8411 0.00948 0.00350 -0.0578 0.3270 1.0000 5.500 0.8915 0.01009 0.00401 -0.0570 0.2855 1.0000 6.000 0.9408 0.01081 0.00456 -0.0560 0.2418 1.0000 6.500 0.9897 0.01157 0.00518 -0.0549 0.2000 1.0000 7.000 1.0374 0.01243 0.00592 -0.0538 0.1587 1.0000 7.500 1.0842 0.01336 0.00673 -0.0525 0.1230 1.0000 8.000 1.1298 0.01438 0.00767 -0.0511 0.0923 1.0000 8.500 1.1725 0.01563 0.00877 -0.0494 0.0596 1.0000 9.000 1.2087 0.01751 0.01043 -0.0467 0.0216 1.0000 9.500 1.2412 0.01961 0.01261 -0.0433 0.0129 1.0000 10.000 1.2720 0.02153 0.01480 -0.0397 0.0115 1.0000 10.500 1.2945 0.02363 0.01713 -0.0350 0.0105 1.0000 11.000 1.3073 0.02594 0.01964 -0.0293 0.0097 1.0000 11.500 1.3119 0.02898 0.02289 -0.0238 0.0090 1.0000 12.000 1.3061 0.03332 0.02752 -0.0186 0.0086 1.0000 12.500 1.2950 0.03898 0.03351 -0.0149 0.0084 1.0000 13.000 1.2901 0.04469 0.03953 -0.0134 0.0083 1.0000 13.500 1.2807 0.05166 0.04686 -0.0134 0.0083 1.0000 14.000 1.2671 0.05996 0.05550 -0.0153 0.0082 1.0000 14.500 1.2507 0.06957 0.06546 -0.0192 0.0081 1.0000 15.000 1.2245 0.08183 0.07806 -0.0250 0.0082 1.0000 15.500 1.1978 0.09549 0.09205 -0.0327 0.0081 1.0000 16.000 1.1641 0.11166 0.10853 -0.0421 0.0082 1.0000 16.500 1.1312 0.12909 0.12625 -0.0527 0.0083 1.0000 18.500 0.7779 0.21591 0.21410 -0.0991 0.0193 1.0000 19.000 0.7889 0.22307 0.22128 -0.1021 0.0187 1.0000 19.500 0.7947 0.23380 0.23200 -0.1058 0.0178 1.0000 20.000 0.8015 0.24285 0.24107 -0.1099 0.0176 1.0000 20.500 0.8054 0.25260 0.25083 -0.1153 0.0159 1.0000 21.000 0.8141 0.26114 0.25939 -0.1190 0.0146 1.0000 21.500 0.8236 0.26894 0.26721 -0.1224 0.0135 1.0000 22.000 0.8342 0.27614 0.27444 -0.1253 0.0130 1.0000 22.500 0.8443 0.28601 0.28432 -0.1279 0.0125 1.0000 23.000 0.8483 0.29574 0.29406 -0.1328 0.0122 1.0000 23.500 0.8549 0.30560 0.30394 -0.1370 0.0112 1.0000 24.000 0.8631 0.31464 0.31299 -0.1405 0.0096 1.0000 24.500 0.8715 0.32263 0.32102 -0.1436 0.0088 1.0000 25.000 0.8798 0.33099 0.32940 -0.1467 0.0086 1.0000 25.500 0.8878 0.34164 0.34007 -0.1495 0.0083 1.0000 26.000 0.8934 0.35129 0.34974 -0.1533 0.0083 1.0000 26.500 0.8988 0.36151 0.35997 -0.1573 0.0082 1.0000 27.000 0.9050 0.37187 0.37034 -0.1611 0.0077 1.0000