XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY RC12-64C AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.5530 0.07841 0.07576 -0.0480 1.0000 0.0146 -10.250 -0.5661 0.07218 0.06946 -0.0527 1.0000 0.0145 -10.000 -0.5816 0.06728 0.06447 -0.0552 1.0000 0.0145 -9.750 -0.6003 0.06327 0.06035 -0.0555 1.0000 0.0145 -9.500 -0.6213 0.06026 0.05725 -0.0532 1.0000 0.0145 -9.250 -0.6460 0.05837 0.05527 -0.0479 1.0000 0.0145 -9.000 -0.6718 0.05673 0.05354 -0.0413 1.0000 0.0145 -8.750 -0.6975 0.05498 0.05163 -0.0345 1.0000 0.0145 -8.500 -0.7210 0.05331 0.04975 -0.0278 1.0000 0.0146 -7.750 -0.6949 0.04331 0.03931 -0.0255 0.9949 0.0148 -7.500 -0.6746 0.04054 0.03649 -0.0262 0.9923 0.0149 -7.250 -0.6538 0.03792 0.03373 -0.0269 0.9892 0.0151 -7.000 -0.6306 0.03534 0.03094 -0.0277 0.9868 0.0154 -6.750 -0.6056 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0.00277 -0.0112 0.6612 0.9462 3.000 0.4192 0.00760 0.00306 -0.0123 0.6336 0.9569 3.250 0.4829 0.00833 0.00362 -0.0194 0.5866 0.9674 3.500 0.5099 0.00863 0.00375 -0.0192 0.5457 0.9737 3.750 0.5431 0.00898 0.00385 -0.0206 0.4881 0.9752 4.000 0.5742 0.00948 0.00403 -0.0217 0.4132 0.9772 4.250 0.6025 0.01014 0.00428 -0.0224 0.3252 0.9800 4.500 0.6278 0.01083 0.00457 -0.0224 0.2459 0.9838 4.750 0.6563 0.01150 0.00487 -0.0232 0.1755 0.9862 5.000 0.6873 0.01212 0.00520 -0.0244 0.1221 0.9880 5.250 0.7184 0.01261 0.00552 -0.0255 0.0969 0.9903 5.500 0.7491 0.01303 0.00586 -0.0265 0.0861 0.9929 5.750 0.7807 0.01333 0.00616 -0.0276 0.0800 0.9950 6.000 0.8132 0.01372 0.00651 -0.0290 0.0744 0.9967 6.250 0.8462 0.01397 0.00677 -0.0305 0.0701 0.9986 6.500 0.8743 0.01443 0.00719 -0.0310 0.0656 1.0000 6.750 0.8928 0.01462 0.00742 -0.0293 0.0630 1.0000 7.000 0.9099 0.01488 0.00768 -0.0274 0.0602 1.0000 7.250 0.9231 0.01540 0.00818 -0.0248 0.0570 1.0000 7.500 0.9399 0.01563 0.00847 -0.0228 0.0548 1.0000 7.750 0.9549 0.01594 0.00879 -0.0205 0.0522 1.0000 8.000 0.9639 0.01662 0.00943 -0.0172 0.0494 1.0000 8.250 0.9800 0.01681 0.00969 -0.0150 0.0474 1.0000 8.500 0.9939 0.01712 0.01003 -0.0125 0.0452 1.0000 8.750 1.0039 0.01765 0.01053 -0.0093 0.0432 1.0000 9.000 1.0159 0.01806 0.01100 -0.0064 0.0415 1.0000 9.250 1.0294 0.01838 0.01137 -0.0038 0.0397 1.0000 9.500 1.0423 0.01875 0.01174 -0.0011 0.0382 1.0000 9.750 1.0505 0.01944 0.01242 0.0022 0.0368 1.0000 10.000 1.0627 0.01980 0.01286 0.0050 0.0356 1.0000 10.250 1.0738 0.02020 0.01331 0.0079 0.0343 1.0000 10.500 1.0864 0.02064 0.01376 0.0104 0.0332 1.0000 10.750 1.0968 0.02136 0.01448 0.0131 0.0321 1.0000 11.000 1.1093 0.02209 0.01528 0.0153 0.0312 1.0000 11.250 1.1233 0.02276 0.01604 0.0172 0.0303 1.0000 11.500 1.1368 0.02349 0.01683 0.0190 0.0295 1.0000 11.750 1.1501 0.02426 0.01764 0.0208 0.0288 1.0000 12.000 1.1623 0.02514 0.01856 0.0225 0.0282 1.0000 12.250 1.1712 0.02644 0.01989 0.0246 0.0275 1.0000 12.500 1.1820 0.02763 0.02118 0.0263 0.0271 1.0000 12.750 1.1934 0.02870 0.02237 0.0279 0.0267 1.0000 13.000 1.2039 0.02989 0.02367 0.0295 0.0263 1.0000 13.250 1.2135 0.03116 0.02505 0.0310 0.0258 1.0000 13.500 1.2224 0.03251 0.02651 0.0325 0.0255 1.0000 13.750 1.2305 0.03394 0.02804 0.0339 0.0251 1.0000 14.000 1.2378 0.03545 0.02965 0.0352 0.0248 1.0000 14.250 1.2442 0.03707 0.03135 0.0364 0.0245 1.0000 14.500 1.2497 0.03882 0.03320 0.0375 0.0243 1.0000 14.750 1.2540 0.04074 0.03520 0.0385 0.0240 1.0000 15.000 1.2563 0.04297 0.03751 0.0395 0.0237 1.0000 15.250 1.2537 0.04592 0.04061 0.0406 0.0234 1.0000 15.500 1.2498 0.04879 0.04366 0.0411 0.0233 1.0000 15.750 1.2456 0.05177 0.04682 0.0413 0.0232 1.0000 16.000 1.2389 0.05516 0.05039 0.0411 0.0230 1.0000 16.250 1.2300 0.05901 0.05443 0.0405 0.0229 1.0000 16.500 1.2187 0.06342 0.05903 0.0394 0.0229 1.0000 16.750 1.2046 0.06846 0.06426 0.0377 0.0228 1.0000 17.000 1.1876 0.07429 0.07029 0.0352 0.0228 1.0000 17.250 1.1673 0.08102 0.07723 0.0319 0.0227 1.0000 17.500 1.1432 0.08885 0.08526 0.0277 0.0228 1.0000 17.750 1.1138 0.09825 0.09488 0.0221 0.0228 1.0000 18.000 1.0761 0.10997 0.10681 0.0149 0.0229 1.0000 18.250 1.0159 0.12768 0.12478 0.0039 0.0232 1.0000