XFOIL Version 6.96 Calculated polar for: NASA/LANGLEY RC-12(B)3 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 -0.6272 0.06360 0.06129 -0.0515 1.0000 0.0245 -10.250 -0.6551 0.05731 0.05489 -0.0522 1.0000 0.0241 -10.000 -0.7099 0.04891 0.04622 -0.0477 1.0000 0.0235 -9.750 -0.7725 0.03349 0.02955 -0.0429 0.9856 0.0232 -9.500 -0.7633 0.02966 0.02520 -0.0416 0.9787 0.0237 -9.250 -0.7487 0.02699 0.02210 -0.0403 0.9719 0.0241 -9.000 -0.7322 0.02524 0.02002 -0.0387 0.9646 0.0244 -8.750 -0.7153 0.02383 0.01832 -0.0369 0.9576 0.0247 -8.500 -0.7007 0.02152 0.01574 -0.0350 0.9506 0.0253 -8.250 -0.6813 0.02059 0.01473 -0.0335 0.9442 0.0259 -8.000 -0.6606 0.01991 0.01395 -0.0322 0.9385 0.0265 -7.750 -0.6390 0.01926 0.01321 -0.0311 0.9323 0.0273 -7.500 -0.6176 0.01868 0.01252 -0.0298 0.9270 0.0282 -7.250 -0.5944 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0.00422 -0.0502 0.6706 1.0000 2.500 0.5985 0.00886 0.00417 -0.0500 0.6567 1.0000 2.750 0.6245 0.00887 0.00414 -0.0498 0.6420 1.0000 3.000 0.6506 0.00890 0.00412 -0.0496 0.6254 1.0000 3.250 0.6765 0.00895 0.00411 -0.0494 0.6062 1.0000 3.500 0.7022 0.00904 0.00412 -0.0492 0.5830 1.0000 3.750 0.7278 0.00915 0.00415 -0.0489 0.5582 1.0000 4.000 0.7532 0.00930 0.00420 -0.0486 0.5327 1.0000 4.250 0.7783 0.00948 0.00428 -0.0483 0.5054 1.0000 4.500 0.8032 0.00968 0.00438 -0.0480 0.4773 1.0000 4.750 0.8277 0.00993 0.00451 -0.0476 0.4475 1.0000 5.000 0.8518 0.01020 0.00467 -0.0472 0.4178 1.0000 5.250 0.8756 0.01050 0.00485 -0.0467 0.3885 1.0000 5.500 0.8989 0.01082 0.00505 -0.0461 0.3592 1.0000 5.750 0.9217 0.01116 0.00527 -0.0455 0.3309 1.0000 6.000 0.9444 0.01150 0.00550 -0.0448 0.3035 1.0000 6.250 0.9666 0.01186 0.00576 -0.0441 0.2770 1.0000 6.500 0.9882 0.01225 0.00604 -0.0432 0.2517 1.0000 6.750 1.0093 0.01266 0.00634 -0.0423 0.2265 1.0000 7.000 1.0300 0.01307 0.00666 -0.0413 0.2027 1.0000 7.500 1.0692 0.01399 0.00739 -0.0389 0.1587 1.0000 7.750 1.0877 0.01449 0.00780 -0.0375 0.1392 1.0000 8.000 1.1054 0.01501 0.00823 -0.0360 0.1215 1.0000 8.250 1.1228 0.01551 0.00867 -0.0343 0.1060 1.0000 8.500 1.1391 0.01605 0.00915 -0.0325 0.0925 1.0000 8.750 1.1543 0.01661 0.00967 -0.0306 0.0809 1.0000 9.000 1.1679 0.01724 0.01024 -0.0283 0.0710 1.0000 9.250 1.1823 0.01774 0.01075 -0.0261 0.0639 1.0000 9.500 1.1942 0.01833 0.01134 -0.0235 0.0578 1.0000 9.750 1.2047 0.01894 0.01194 -0.0207 0.0528 1.0000 10.000 1.2129 0.01957 0.01261 -0.0175 0.0489 1.0000 10.250 1.2198 0.02009 0.01316 -0.0139 0.0458 1.0000 10.500 1.2168 0.02070 0.01378 -0.0087 0.0434 1.0000 10.750 1.2139 0.02144 0.01456 -0.0036 0.0413 1.0000 11.000 1.2187 0.02200 0.01520 -0.0001 0.0394 1.0000 11.250 1.2225 0.02268 0.01592 0.0035 0.0375 1.0000 11.500 1.2231 0.02360 0.01685 0.0072 0.0357 1.0000 11.750 1.2218 0.02470 0.01802 0.0111 0.0341 1.0000 12.000 1.2281 0.02547 0.01886 0.0139 0.0328 1.0000 12.250 1.2331 0.02636 0.01982 0.0166 0.0314 1.0000 12.500 1.2369 0.02739 0.02088 0.0193 0.0301 1.0000 12.750 1.2346 0.02890 0.02242 0.0224 0.0288 1.0000 13.000 1.2365 0.03023 0.02384 0.0249 0.0278 1.0000 13.250 1.2426 0.03136 0.02505 0.0268 0.0267 1.0000 13.500 1.2470 0.03268 0.02644 0.0287 0.0257 1.0000 13.750 1.2506 0.03414 0.02797 0.0305 0.0247 1.0000 14.000 1.2499 0.03603 0.02990 0.0323 0.0239 1.0000 14.250 1.2428 0.03858 0.03251 0.0342 0.0231 1.0000 14.500 1.2483 0.04017 0.03422 0.0352 0.0224 1.0000 14.750 1.2517 0.04203 0.03618 0.0362 0.0216 1.0000 15.000 1.2540 0.04408 0.03831 0.0369 0.0209 1.0000 15.250 1.2557 0.04631 0.04061 0.0374 0.0202 1.0000 15.500 1.2548 0.04892 0.04329 0.0378 0.0196 1.0000 15.750 1.2476 0.05227 0.04670 0.0381 0.0190 1.0000 16.000 1.2442 0.05538 0.04993 0.0382 0.0185 1.0000 16.250 1.2443 0.05828 0.05295 0.0379 0.0181 1.0000 16.500 1.2426 0.06145 0.05624 0.0375 0.0176 1.0000 16.750 1.2399 0.06486 0.05976 0.0369 0.0172 1.0000 17.000 1.2364 0.06846 0.06346 0.0360 0.0168 1.0000 17.250 1.2323 0.07225 0.06734 0.0350 0.0165 1.0000 17.500 1.2273 0.07623 0.07141 0.0338 0.0161 1.0000 17.750 1.2210 0.08045 0.07572 0.0325 0.0159 1.0000 18.000 1.2132 0.08492 0.08026 0.0310 0.0156 1.0000 18.250 1.2028 0.08966 0.08507 0.0297 0.0152 1.0000 18.500 1.1934 0.09450 0.09004 0.0280 0.0150 1.0000 18.750 1.1855 0.09943 0.09511 0.0260 0.0149 1.0000 19.000 1.1767 0.10458 0.10040 0.0238 0.0147 1.0000 19.250 1.1672 0.10991 0.10586 0.0214 0.0145 1.0000