XFOIL Version 6.96 Calculated polar for: LOCKHEED-GEORGIA SUPERCRITICAL 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 ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5543 0.08461 0.08116 -0.0179 1.0000 0.0470 -8.500 -0.5674 0.07844 0.07497 -0.0240 1.0000 0.0474 -8.250 -0.5839 0.07322 0.06961 -0.0271 1.0000 0.0485 -7.500 -0.5986 0.05958 0.05552 -0.0266 1.0000 0.0512 -7.250 -0.5886 0.05675 0.05273 -0.0256 1.0000 0.0523 -7.000 -0.5807 0.05409 0.05001 -0.0243 1.0000 0.0539 -6.750 -0.5738 0.05133 0.04712 -0.0226 1.0000 0.0563 -6.250 -0.5664 0.04493 0.04010 -0.0177 1.0000 0.0634 -6.000 -0.5540 0.04251 0.03771 -0.0161 1.0000 0.0653 -5.750 -0.5423 0.04048 0.03555 -0.0140 1.0000 0.0688 -5.500 -0.5354 0.03814 0.03276 -0.0110 1.0000 0.0764 -5.250 -0.5211 0.03583 0.03049 -0.0094 1.0000 0.0792 -5.000 -0.5101 0.03445 0.02872 -0.0067 1.0000 0.0899 -4.750 -0.4824 0.02571 0.01876 -0.0017 1.0000 0.0374 -4.500 -0.4627 0.02375 0.01651 0.0002 1.0000 0.0371 -4.250 -0.4417 0.02218 0.01469 0.0018 1.0000 0.0375 -4.000 -0.4190 0.02046 0.01274 0.0032 1.0000 0.0367 -3.750 -0.3957 0.01906 0.01116 0.0045 1.0000 0.0365 -3.500 -0.3724 0.01795 0.00996 0.0056 1.0000 0.0371 -3.250 -0.3494 0.01706 0.00900 0.0067 1.0000 0.0384 -3.000 -0.3265 0.01613 0.00805 0.0077 1.0000 0.0409 -2.750 -0.3043 0.01548 0.00747 0.0085 1.0000 0.0455 -2.500 -0.2816 0.01498 0.00695 0.0094 1.0000 0.0495 -2.250 -0.2382 0.01398 0.00604 0.0060 0.9951 0.0658 -2.000 -0.2063 0.01042 0.00529 0.0041 0.9895 0.6656 -1.750 -0.1706 0.01017 0.00571 0.0048 0.9813 0.8729 -1.500 -0.1234 0.01058 0.00611 0.0029 0.9758 0.9442 -1.250 -0.0290 0.01130 0.00664 -0.0086 0.9849 0.9828 -1.000 0.0453 0.01130 0.00650 -0.0178 0.9848 0.9941 -0.750 0.1061 0.01107 0.00618 -0.0246 0.9777 0.9976 -0.500 0.1605 0.01080 0.00584 -0.0302 0.9674 1.0000 -0.250 0.2023 0.01051 0.00550 -0.0331 0.9499 1.0000 0.000 0.2375 0.01022 0.00516 -0.0345 0.9289 1.0000 0.250 0.2629 0.00999 0.00487 -0.0338 0.9017 1.0000 0.500 0.2854 0.00980 0.00459 -0.0323 0.8722 1.0000 0.750 0.3069 0.00965 0.00434 -0.0307 0.8395 1.0000 1.000 0.3286 0.00957 0.00412 -0.0291 0.8011 1.0000 1.250 0.3508 0.00955 0.00392 -0.0275 0.7558 1.0000 1.500 0.3731 0.00964 0.00375 -0.0261 0.7006 1.0000 1.750 0.3953 0.00985 0.00363 -0.0248 0.6310 1.0000 2.000 0.4170 0.01020 0.00357 -0.0235 0.5507 1.0000 2.250 0.4382 0.01065 0.00360 -0.0224 0.4737 1.0000 2.500 0.4596 0.01110 0.00371 -0.0214 0.4151 1.0000 2.750 0.4814 0.01152 0.00386 -0.0204 0.3757 1.0000 3.000 0.5035 0.01188 0.00403 -0.0195 0.3476 1.0000 3.250 0.5259 0.01221 0.00423 -0.0186 0.3258 1.0000 3.500 0.5482 0.01253 0.00443 -0.0177 0.3077 1.0000 3.750 0.5706 0.01286 0.00468 -0.0168 0.2928 1.0000 4.000 0.5930 0.01320 0.00493 -0.0158 0.2802 1.0000 4.250 0.6153 0.01358 0.00520 -0.0149 0.2688 1.0000 4.500 0.6380 0.01388 0.00549 -0.0140 0.2577 1.0000 4.750 0.6607 0.01423 0.00582 -0.0131 0.2477 1.0000 5.000 0.6832 0.01469 0.00617 -0.0122 0.2394 1.0000 5.250 0.7063 0.01498 0.00651 -0.0113 0.2307 1.0000 5.500 0.7290 0.01545 0.00692 -0.0105 0.2231 1.0000 5.750 0.7521 0.01576 0.00728 -0.0096 0.2151 1.0000 6.000 0.7750 0.01629 0.00774 -0.0088 0.2085 1.0000 6.250 0.7983 0.01664 0.00820 -0.0080 0.2017 1.0000 6.500 0.8215 0.01718 0.00866 -0.0073 0.1958 1.0000 6.750 0.8448 0.01759 0.00919 -0.0065 0.1895 1.0000 7.000 0.8682 0.01802 0.00962 -0.0058 0.1836 1.0000 7.250 0.8918 0.01868 0.01031 -0.0051 0.1786 1.0000 7.500 0.9154 0.01915 0.01091 -0.0044 0.1732 1.0000 7.750 0.9391 0.01966 0.01140 -0.0038 0.1683 1.0000 8.000 0.9623 0.02034 0.01218 -0.0032 0.1632 1.0000 8.250 0.9853 0.02072 0.01269 -0.0025 0.1574 1.0000 8.500 1.0086 0.02139 0.01325 -0.0020 0.1517 1.0000 8.750 1.0303 0.02167 0.01379 -0.0011 0.1460 1.0000 9.000 1.0530 0.02206 0.01422 -0.0004 0.1408 1.0000 9.250 1.0749 0.02273 0.01498 0.0003 0.1356 1.0000 9.500 1.0964 0.02307 0.01547 0.0012 0.1297 1.0000 9.750 1.1180 0.02369 0.01603 0.0018 0.1241 1.0000 10.000 1.1379 0.02398 0.01660 0.0029 0.1178 1.0000 10.250 1.1582 0.02449 0.01704 0.0037 0.1116 1.0000 10.500 1.1768 0.02481 0.01764 0.0049 0.1046 1.0000 10.750 1.1947 0.02535 0.01819 0.0061 0.0976 1.0000 11.000 1.2119 0.02571 0.01872 0.0074 0.0892 1.0000 11.250 1.2272 0.02648 0.01964 0.0088 0.0804 1.0000 11.500 1.2402 0.02743 0.02062 0.0105 0.0725 1.0000 11.750 1.2519 0.02840 0.02162 0.0122 0.0654 1.0000 12.000 1.2619 0.02968 0.02307 0.0142 0.0595 1.0000 12.250 1.2664 0.03099 0.02438 0.0167 0.0552 1.0000 12.500 1.2705 0.03256 0.02613 0.0191 0.0516 1.0000 12.750 1.2742 0.03407 0.02776 0.0212 0.0484 1.0000 13.000 1.2735 0.03610 0.02981 0.0232 0.0460 1.0000 13.250 1.2724 0.03843 0.03232 0.0248 0.0441 1.0000 13.500 1.2715 0.04076 0.03486 0.0259 0.0422 1.0000 13.750 1.2697 0.04330 0.03753 0.0265 0.0404 1.0000 14.000 1.2664 0.04616 0.04047 0.0266 0.0390 1.0000 14.250 1.2605 0.04962 0.04396 0.0267 0.0376 1.0000 14.500 1.2522 0.05362 0.04816 0.0260 0.0368 1.0000 14.750 1.2429 0.05800 0.05277 0.0244 0.0361 1.0000 15.000 1.2316 0.06296 0.05795 0.0222 0.0355 1.0000 15.250 1.2181 0.06850 0.06370 0.0194 0.0350 1.0000 15.500 1.2029 0.07461 0.07000 0.0160 0.0345 1.0000 15.750 1.1853 0.08131 0.07689 0.0122 0.0342 1.0000 16.000 1.1652 0.08874 0.08450 0.0079 0.0341 1.0000 16.250 1.1412 0.09718 0.09313 0.0030 0.0341 1.0000 16.500 1.1117 0.10707 0.10321 -0.0029 0.0345 1.0000 16.750 1.0710 0.11986 0.11619 -0.0105 0.0354 1.0000 17.000 1.0166 0.13660 0.13307 -0.0204 0.0367 1.0000