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 = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5457 0.10274 0.09784 -0.0080 1.0000 0.1003 -9.000 -0.5743 0.09713 0.09232 -0.0188 1.0000 0.1017 -8.750 -0.6047 0.09336 0.08847 -0.0233 1.0000 0.1022 -8.500 -0.5449 0.09008 0.08532 -0.0124 1.0000 0.1084 -8.250 -0.5521 0.08558 0.08088 -0.0161 1.0000 0.1120 -8.000 -0.5816 0.08085 0.07607 -0.0221 1.0000 0.1157 -7.750 -0.5907 0.07589 0.07106 -0.0234 1.0000 0.1185 -7.500 -0.5702 0.07294 0.06823 -0.0208 1.0000 0.1232 -6.750 -0.5144 0.05156 0.04713 -0.0215 1.0000 0.1591 -6.500 -0.5112 0.04785 0.04348 -0.0196 1.0000 0.1680 -6.250 -0.5634 0.05732 0.05219 -0.0178 1.0000 0.1751 -6.000 -0.5531 0.05413 0.04911 -0.0158 1.0000 0.1875 -5.750 -0.5510 0.05158 0.04646 -0.0138 1.0000 0.2092 -5.500 -0.5402 0.04894 0.04390 -0.0115 1.0000 0.2265 -5.000 -0.4953 0.03411 0.02645 -0.0087 1.0000 0.0779 -4.750 -0.4747 0.03112 0.02300 -0.0064 1.0000 0.0684 -4.500 -0.4528 0.02892 0.01999 -0.0037 1.0000 0.0620 -4.250 -0.4308 0.02723 0.01803 -0.0020 1.0000 0.0611 -4.000 -0.4087 0.02496 0.01556 -0.0007 1.0000 0.0624 -3.750 -0.3861 0.02327 0.01386 0.0003 1.0000 0.0656 -3.500 -0.3622 0.02190 0.01240 0.0015 1.0000 0.0676 -3.250 -0.3383 0.02068 0.01112 0.0027 1.0000 0.0703 -3.000 -0.3154 0.01955 0.00997 0.0039 1.0000 0.0760 -2.750 -0.2940 0.01857 0.00910 0.0052 1.0000 0.0850 -2.500 -0.2731 0.01755 0.00817 0.0066 1.0000 0.0985 -2.250 -0.2517 0.01581 0.00709 0.0077 1.0000 0.1847 -2.000 -0.0243 0.01478 0.00825 -0.0217 1.0000 1.0000 -1.750 -0.0194 0.01458 0.00799 -0.0186 1.0000 1.0000 -1.500 -0.0174 0.01446 0.00781 -0.0150 1.0000 1.0000 -1.250 -0.0178 0.01439 0.00770 -0.0108 1.0000 1.0000 -1.000 -0.0193 0.01439 0.00764 -0.0065 1.0000 1.0000 -0.750 -0.0201 0.01443 0.00764 -0.0023 1.0000 1.0000 -0.500 -0.0188 0.01454 0.00768 0.0015 1.0000 1.0000 -0.250 -0.0147 0.01472 0.00779 0.0047 1.0000 1.0000 0.000 0.0494 0.01493 0.00791 -0.0031 0.9877 1.0000 0.250 0.1171 0.01501 0.00791 -0.0112 0.9739 1.0000 0.500 0.1859 0.01489 0.00777 -0.0193 0.9591 1.0000 0.750 0.2514 0.01458 0.00747 -0.0263 0.9415 1.0000 1.000 0.3040 0.01417 0.00709 -0.0304 0.9177 1.0000 1.250 0.3448 0.01376 0.00669 -0.0319 0.8879 1.0000 1.500 0.3767 0.01339 0.00629 -0.0314 0.8521 1.0000 1.750 0.4011 0.01314 0.00596 -0.0295 0.8060 1.0000 2.000 0.4228 0.01302 0.00566 -0.0270 0.7471 1.0000 2.250 0.4433 0.01312 0.00542 -0.0244 0.6696 1.0000 2.500 0.4626 0.01352 0.00532 -0.0219 0.5796 1.0000 2.750 0.4821 0.01413 0.00543 -0.0200 0.5058 1.0000 3.000 0.5026 0.01477 0.00566 -0.0185 0.4558 1.0000 3.250 0.5240 0.01537 0.00596 -0.0173 0.4205 1.0000 3.500 0.5460 0.01595 0.00631 -0.0162 0.3934 1.0000 3.750 0.5684 0.01650 0.00673 -0.0153 0.3709 1.0000 4.000 0.5911 0.01706 0.00717 -0.0144 0.3523 1.0000 4.250 0.6140 0.01764 0.00764 -0.0135 0.3362 1.0000 4.500 0.6370 0.01822 0.00815 -0.0126 0.3216 1.0000 4.750 0.6602 0.01884 0.00874 -0.0118 0.3088 1.0000 5.000 0.6837 0.01951 0.00933 -0.0111 0.2977 1.0000 5.250 0.7071 0.02014 0.00991 -0.0103 0.2867 1.0000 5.500 0.7301 0.02079 0.01066 -0.0095 0.2759 1.0000 5.750 0.7539 0.02157 0.01141 -0.0089 0.2673 1.0000 6.000 0.7772 0.02228 0.01219 -0.0081 0.2584 1.0000 6.250 0.8005 0.02313 0.01310 -0.0074 0.2502 1.0000 6.500 0.8239 0.02387 0.01388 -0.0067 0.2422 1.0000 6.750 0.8468 0.02485 0.01502 -0.0060 0.2352 1.0000 7.000 0.8700 0.02574 0.01600 -0.0053 0.2283 1.0000 7.250 0.8928 0.02682 0.01720 -0.0046 0.2220 1.0000 7.500 0.9146 0.02776 0.01834 -0.0038 0.2149 1.0000 7.750 0.9390 0.02895 0.01945 -0.0034 0.2097 1.0000 8.000 0.9573 0.03026 0.02124 -0.0021 0.2036 1.0000 8.250 0.9802 0.03121 0.02225 -0.0015 0.1976 1.0000 8.500 0.9993 0.03272 0.02402 -0.0005 0.1919 1.0000 8.750 1.0184 0.03393 0.02548 0.0006 0.1854 1.0000 9.000 1.0403 0.03494 0.02648 0.0012 0.1789 1.0000 9.250 1.0561 0.03607 0.02797 0.0026 0.1711 1.0000 9.500 1.0779 0.03695 0.02882 0.0032 0.1645 1.0000 9.750 1.0917 0.03821 0.03046 0.0049 0.1568 1.0000 10.000 1.1117 0.03912 0.03138 0.0057 0.1500 1.0000 10.250 1.1260 0.04007 0.03260 0.0072 0.1417 1.0000 10.500 1.1388 0.04145 0.03417 0.0087 0.1344 1.0000 10.750 1.1628 0.04119 0.03377 0.0093 0.1256 1.0000 11.000 1.1627 0.04363 0.03672 0.0120 0.1182 1.0000 11.250 1.1848 0.04372 0.03662 0.0127 0.1102 1.0000 11.500 1.1822 0.04601 0.03936 0.0155 0.1037 1.0000 11.750 1.1980 0.04684 0.04012 0.0167 0.0973 1.0000 12.000 1.1835 0.05016 0.04393 0.0199 0.0935 1.0000 12.250 1.2129 0.04983 0.04323 0.0201 0.0864 1.0000 12.500 1.1880 0.05353 0.04742 0.0239 0.0851 1.0000 12.750 1.1598 0.05770 0.05193 0.0266 0.0844 1.0000 13.000 1.1280 0.06298 0.05750 0.0270 0.0843 1.0000 13.250 1.0923 0.06984 0.06459 0.0248 0.0849 1.0000 13.500 1.0540 0.07859 0.07347 0.0200 0.0859 1.0000