XFOIL Version 6.96 Calculated polar for: GIII BL126 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.6317 0.12480 0.12321 0.0171 1.0000 0.0030 -11.250 -0.6338 0.11931 0.11773 0.0149 1.0000 0.0030 -10.750 -0.9819 0.03141 0.02870 -0.0224 1.0000 0.0024 -10.500 -0.9787 0.02695 0.02378 -0.0207 1.0000 0.0025 -10.250 -0.9656 0.02441 0.02094 -0.0195 1.0000 0.0026 -10.000 -0.9479 0.02276 0.01906 -0.0187 1.0000 0.0027 -9.750 -0.9282 0.02145 0.01757 -0.0179 1.0000 0.0028 -9.500 -0.9073 0.02036 0.01633 -0.0172 1.0000 0.0030 -9.250 -0.8859 0.01935 0.01519 -0.0166 1.0000 0.0031 -9.000 -0.8642 0.01837 0.01407 -0.0159 1.0000 0.0032 -8.750 -0.8423 0.01743 0.01298 -0.0152 1.0000 0.0034 -8.500 -0.8202 0.01656 0.01198 -0.0144 1.0000 0.0036 -8.250 -0.7952 0.01571 0.01099 -0.0143 0.9965 0.0038 -8.000 -0.7639 0.01486 0.01000 -0.0155 0.9818 0.0039 -7.750 -0.7308 0.01413 0.00910 -0.0170 0.9586 0.0041 -7.500 -0.7038 0.01360 0.00840 -0.0170 0.9225 0.0042 -7.250 -0.6819 0.01281 0.00739 -0.0159 0.8898 0.0046 -7.000 -0.6579 0.01237 0.00682 -0.0153 0.8672 0.0050 -6.750 -0.6327 0.01207 0.00642 -0.0149 0.8507 0.0055 -6.500 -0.6070 0.01180 0.00607 -0.0146 0.8381 0.0060 -6.250 -0.5810 0.01152 0.00571 -0.0144 0.8280 0.0066 -6.000 -0.5548 0.01124 0.00535 -0.0141 0.8202 0.0070 -5.750 -0.5292 0.01080 0.00479 -0.0138 0.8134 0.0075 -5.500 -0.5034 0.01038 0.00431 -0.0135 0.8075 0.0085 -5.250 -0.4770 0.01011 0.00401 -0.0134 0.8016 0.0093 -5.000 -0.4504 0.00987 0.00371 -0.0132 0.7966 0.0101 -4.750 -0.4235 0.00966 0.00346 -0.0131 0.7919 0.0110 -4.500 -0.3965 0.00948 0.00322 -0.0130 0.7874 0.0115 -4.250 -0.3702 0.00913 0.00279 -0.0127 0.7833 0.0133 -4.000 -0.3433 0.00888 0.00254 -0.0126 0.7791 0.0154 -3.750 -0.3163 0.00870 0.00233 -0.0125 0.7746 0.0176 -3.500 -0.2892 0.00852 0.00212 -0.0124 0.7706 0.0214 -3.250 -0.2621 0.00832 0.00193 -0.0124 0.7670 0.0281 -3.000 -0.2349 0.00813 0.00177 -0.0123 0.7629 0.0389 -2.750 -0.2078 0.00795 0.00163 -0.0122 0.7587 0.0534 -2.500 -0.1808 0.00777 0.00151 -0.0122 0.7548 0.0719 -2.250 -0.1533 0.00762 0.00140 -0.0122 0.7506 0.0867 -2.000 -0.1260 0.00747 0.00129 -0.0122 0.7463 0.1057 -1.500 -0.0716 0.00714 0.00112 -0.0121 0.7359 0.1612 -1.250 -0.0454 0.00686 0.00102 -0.0120 0.7284 0.2247 -1.000 -0.0195 0.00650 0.00092 -0.0118 0.7199 0.3130 -0.750 0.0010 0.00548 0.00073 -0.0109 0.7116 0.5760 -0.500 0.0259 0.00517 0.00069 -0.0104 0.7016 0.6637 -0.250 0.0522 0.00504 0.00067 -0.0100 0.6905 0.7094 0.000 0.0790 0.00499 0.00066 -0.0098 0.6776 0.7394 0.250 0.1057 0.00495 0.00066 -0.0095 0.6636 0.7656 0.500 0.1329 0.00495 0.00066 -0.0094 0.6509 0.7833 0.750 0.1597 0.00494 0.00068 -0.0091 0.6388 0.8043 1.000 0.1858 0.00491 0.00071 -0.0087 0.6265 0.8327 1.250 0.2126 0.00492 0.00075 -0.0085 0.6137 0.8510 1.500 0.2401 0.00497 0.00078 -0.0084 0.5998 0.8580 1.750 0.2676 0.00503 0.00082 -0.0084 0.5850 0.8656 2.000 0.2948 0.00510 0.00087 -0.0083 0.5674 0.8728 2.250 0.3216 0.00524 0.00093 -0.0081 0.5368 0.8809 2.500 0.3463 0.00561 0.00104 -0.0077 0.4542 0.8895 2.750 0.3706 0.00608 0.00121 -0.0072 0.3706 0.8988 3.000 0.3963 0.00636 0.00136 -0.0070 0.3269 0.9085 3.250 0.4218 0.00667 0.00152 -0.0067 0.2791 0.9184 3.500 0.4467 0.00708 0.00172 -0.0063 0.2167 0.9288 3.750 0.4718 0.00751 0.00193 -0.0061 0.1590 0.9396 4.000 0.4978 0.00788 0.00216 -0.0059 0.1160 0.9503 4.250 0.5255 0.00824 0.00239 -0.0062 0.0813 0.9594 4.500 0.5544 0.00857 0.00264 -0.0067 0.0580 0.9676 4.750 0.5837 0.00887 0.00288 -0.0073 0.0412 0.9752 5.000 0.6146 0.00921 0.00314 -0.0082 0.0276 0.9805 5.250 0.6448 0.00947 0.00340 -0.0090 0.0217 0.9861 5.500 0.6763 0.00979 0.00370 -0.0101 0.0164 0.9899 5.750 0.7071 0.01004 0.00400 -0.0110 0.0151 0.9939 6.000 0.7384 0.01034 0.00431 -0.0121 0.0134 0.9966 6.250 0.7694 0.01071 0.00468 -0.0131 0.0111 0.9994 6.500 0.7937 0.01107 0.00508 -0.0126 0.0099 1.0000 6.750 0.8168 0.01134 0.00539 -0.0119 0.0094 1.0000 7.000 0.8399 0.01165 0.00574 -0.0112 0.0085 1.0000 7.250 0.8630 0.01199 0.00610 -0.0105 0.0076 1.0000 7.500 0.8857 0.01244 0.00656 -0.0097 0.0065 1.0000 7.750 0.9089 0.01285 0.00701 -0.0091 0.0059 1.0000 8.000 0.9325 0.01322 0.00743 -0.0086 0.0054 1.0000 8.250 0.9559 0.01365 0.00790 -0.0080 0.0050 1.0000 8.500 0.9791 0.01411 0.00839 -0.0075 0.0045 1.0000 8.750 1.0018 0.01465 0.00896 -0.0069 0.0041 1.0000 9.000 1.0226 0.01548 0.00992 -0.0060 0.0037 1.0000 9.250 1.0446 0.01612 0.01064 -0.0054 0.0035 1.0000 9.500 1.0666 0.01674 0.01134 -0.0047 0.0034 1.0000 9.750 1.0880 0.01742 0.01212 -0.0040 0.0033 1.0000 10.000 1.1089 0.01817 0.01296 -0.0033 0.0031 1.0000 10.250 1.1294 0.01895 0.01384 -0.0026 0.0029 1.0000 10.500 1.1492 0.01978 0.01477 -0.0018 0.0028 1.0000 10.750 1.1687 0.02062 0.01572 -0.0009 0.0026 1.0000 11.000 1.1879 0.02144 0.01663 -0.0001 0.0025 1.0000 11.250 1.2066 0.02227 0.01755 0.0007 0.0024 1.0000 11.500 1.2241 0.02321 0.01860 0.0016 0.0022 1.0000 11.750 1.2387 0.02440 0.01992 0.0028 0.0021 1.0000 12.000 1.2475 0.02615 0.02187 0.0046 0.0020 1.0000 12.250 1.2481 0.02835 0.02431 0.0073 0.0019 1.0000 12.500 1.2536 0.02985 0.02597 0.0093 0.0019 1.0000 12.750 1.2564 0.03163 0.02791 0.0111 0.0018 1.0000 13.000 1.2572 0.03368 0.03012 0.0126 0.0018 1.0000 13.250 1.2556 0.03610 0.03272 0.0136 0.0018 1.0000 13.500 1.2520 0.03892 0.03572 0.0142 0.0018 1.0000 13.750 1.2453 0.04229 0.03927 0.0142 0.0018 1.0000 14.000 1.2356 0.04627 0.04343 0.0136 0.0018 1.0000 14.250 1.2227 0.05103 0.04838 0.0121 0.0018 1.0000 14.500 1.2061 0.05685 0.05438 0.0094 0.0018 1.0000 14.750 1.1847 0.06417 0.06188 0.0053 0.0018 1.0000 15.000 1.1574 0.07374 0.07164 -0.0008 0.0018 1.0000 15.250 1.1194 0.08728 0.08537 -0.0094 0.0018 1.0000