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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.3511 0.09922 0.09583 -0.0354 1.0000 0.0654 -10.250 -0.4977 0.09828 0.09477 -0.0364 1.0000 0.0630 -10.000 -0.4837 0.09601 0.09250 -0.0337 1.0000 0.0639 -9.750 -0.4754 0.09319 0.08968 -0.0335 1.0000 0.0649 -9.500 -0.4719 0.08972 0.08624 -0.0348 1.0000 0.0661 -9.250 -0.4735 0.08548 0.08203 -0.0376 1.0000 0.0675 -9.000 -0.4830 0.08032 0.07690 -0.0423 1.0000 0.0687 -8.750 -0.5002 0.07611 0.07269 -0.0439 1.0000 0.0698 -8.500 -0.5313 0.07459 0.07122 -0.0388 1.0000 0.0698 -8.250 -0.5623 0.07334 0.06999 -0.0328 1.0000 0.0699 -8.000 -0.5891 0.07160 0.06823 -0.0277 1.0000 0.0705 -7.500 -0.5871 0.05922 0.05526 -0.0325 0.9876 0.0760 -7.250 -0.5617 0.05677 0.05283 -0.0341 0.9846 0.0781 -7.000 -0.5909 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-0.0543 0.7415 1.0000 2.750 0.6300 0.01254 0.00645 -0.0535 0.7285 1.0000 3.000 0.6543 0.01247 0.00635 -0.0526 0.7145 1.0000 3.250 0.6786 0.01241 0.00626 -0.0518 0.6996 1.0000 3.500 0.7031 0.01238 0.00623 -0.0510 0.6842 1.0000 3.750 0.7275 0.01238 0.00620 -0.0502 0.6675 1.0000 4.000 0.7518 0.01239 0.00618 -0.0494 0.6493 1.0000 4.250 0.7759 0.01243 0.00617 -0.0486 0.6292 1.0000 4.500 0.7997 0.01250 0.00621 -0.0478 0.6055 1.0000 4.750 0.8232 0.01262 0.00624 -0.0469 0.5812 1.0000 5.000 0.8464 0.01279 0.00635 -0.0460 0.5541 1.0000 5.250 0.8691 0.01301 0.00651 -0.0450 0.5259 1.0000 5.500 0.8912 0.01330 0.00669 -0.0440 0.4964 1.0000 5.750 0.9126 0.01363 0.00691 -0.0429 0.4656 1.0000 6.000 0.9333 0.01402 0.00720 -0.0418 0.4346 1.0000 6.250 0.9532 0.01445 0.00751 -0.0405 0.4037 1.0000 6.500 0.9723 0.01493 0.00787 -0.0391 0.3732 1.0000 6.750 0.9906 0.01543 0.00826 -0.0376 0.3435 1.0000 7.000 1.0079 0.01598 0.00870 -0.0359 0.3146 1.0000 7.250 1.0245 0.01654 0.00917 -0.0342 0.2860 1.0000 7.500 1.0402 0.01713 0.00967 -0.0323 0.2582 1.0000 7.750 1.0547 0.01777 0.01021 -0.0302 0.2315 1.0000 8.000 1.0676 0.01847 0.01081 -0.0279 0.2065 1.0000 8.250 1.0795 0.01919 0.01143 -0.0254 0.1823 1.0000 8.500 1.0897 0.01998 0.01213 -0.0226 0.1613 1.0000 8.750 1.0988 0.02079 0.01286 -0.0196 0.1426 1.0000 9.000 1.1060 0.02164 0.01364 -0.0163 0.1269 1.0000 9.250 1.1117 0.02249 0.01447 -0.0128 0.1141 1.0000 9.500 1.1139 0.02338 0.01532 -0.0087 0.1041 1.0000 9.750 1.1110 0.02425 0.01613 -0.0037 0.0966 1.0000 10.000 1.1122 0.02507 0.01701 0.0005 0.0896 1.0000 10.250 1.1109 0.02613 0.01801 0.0048 0.0839 1.0000 10.500 1.1147 0.02708 0.01904 0.0082 0.0784 1.0000 10.750 1.1178 0.02809 0.02006 0.0115 0.0736 1.0000 11.000 1.1205 0.02940 0.02137 0.0147 0.0695 1.0000 11.250 1.1266 0.03041 0.02247 0.0174 0.0656 1.0000 11.500 1.1312 0.03158 0.02365 0.0200 0.0622 1.0000 11.750 1.1373 0.03305 0.02513 0.0224 0.0590 1.0000 12.000 1.1439 0.03420 0.02641 0.0247 0.0561 1.0000 12.250 1.1500 0.03544 0.02769 0.0268 0.0535 1.0000 12.500 1.1588 0.03708 0.02927 0.0286 0.0506 1.0000 12.750 1.1649 0.03849 0.03085 0.0306 0.0487 1.0000 13.000 1.1701 0.03996 0.03246 0.0326 0.0466 1.0000 13.250 1.1753 0.04144 0.03402 0.0343 0.0447 1.0000 13.500 1.1824 0.04302 0.03557 0.0358 0.0429 1.0000 13.750 1.1890 0.04516 0.03783 0.0373 0.0411 1.0000 14.000 1.1893 0.04709 0.03997 0.0390 0.0398 1.0000 14.250 1.1907 0.04917 0.04223 0.0405 0.0385 1.0000 14.500 1.1914 0.05132 0.04451 0.0417 0.0373 1.0000 14.750 1.1932 0.05340 0.04667 0.0427 0.0362 1.0000 15.000 1.2006 0.05565 0.04890 0.0436 0.0348 1.0000 15.250 1.1933 0.05902 0.05249 0.0446 0.0341 1.0000 15.500 1.1823 0.06237 0.05609 0.0451 0.0336 1.0000 15.750 1.1706 0.06609 0.06006 0.0452 0.0330 1.0000 16.000 1.1580 0.07018 0.06437 0.0449 0.0325 1.0000 16.250 1.1442 0.07470 0.06911 0.0442 0.0320 1.0000 16.500 1.1286 0.07977 0.07440 0.0429 0.0317 1.0000 16.750 1.1104 0.08550 0.08035 0.0410 0.0315 1.0000 17.000 1.0887 0.09215 0.08722 0.0382 0.0314 1.0000 17.250 1.0621 0.10016 0.09546 0.0343 0.0316 1.0000 17.500 1.0288 0.11004 0.10559 0.0288 0.0319 1.0000 17.750 0.9877 0.12250 0.11829 0.0215 0.0326 1.0000 18.000 0.9395 0.13785 0.13382 0.0124 0.0337 1.0000