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 = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5850 0.08138 0.07980 -0.0142 1.0000 0.0113 -9.000 -0.6001 0.07263 0.07104 -0.0242 1.0000 0.0112 -8.750 -0.6178 0.06673 0.06507 -0.0268 1.0000 0.0111 -8.500 -0.6281 0.06037 0.05857 -0.0284 1.0000 0.0115 -8.250 -0.6358 0.05088 0.04873 -0.0282 1.0000 0.0122 -8.000 -0.6398 0.04608 0.04368 -0.0261 1.0000 0.0122 -7.750 -0.6601 0.03898 0.03618 -0.0218 1.0000 0.0124 -7.500 -0.6600 0.03585 0.03290 -0.0187 1.0000 0.0126 -7.250 -0.6523 0.03420 0.03117 -0.0161 1.0000 0.0127 -7.000 -0.6445 0.03261 0.02947 -0.0132 1.0000 0.0129 -6.750 -0.6308 0.03081 0.02754 -0.0116 0.9995 0.0131 -6.500 -0.6040 0.02855 0.02509 -0.0125 0.9979 0.0134 -6.250 -0.5879 0.01765 0.01275 -0.0093 0.9955 0.0094 -6.000 -0.5556 0.01641 0.01134 -0.0103 0.9944 0.0093 -5.750 -0.5263 0.01478 0.00954 -0.0107 0.9922 0.0094 -5.500 -0.4972 0.01300 0.00762 -0.0112 0.9901 0.0097 -5.250 -0.4647 0.01224 0.00684 -0.0124 0.9882 0.0101 -5.000 -0.4303 0.01168 0.00624 -0.0138 0.9866 0.0107 -4.750 -0.3952 0.01112 0.00565 -0.0154 0.9853 0.0112 -4.500 -0.3630 0.01062 0.00512 -0.0164 0.9818 0.0117 -4.250 -0.3296 0.01020 0.00466 -0.0174 0.9753 0.0121 -4.000 -0.3027 0.00948 0.00388 -0.0170 0.9636 0.0129 -3.750 -0.2764 0.00913 0.00351 -0.0165 0.9520 0.0138 -3.500 -0.2499 0.00889 0.00325 -0.0160 0.9427 0.0151 -3.250 -0.2246 0.00855 0.00287 -0.0153 0.9312 0.0167 -3.000 -0.1986 0.00832 0.00261 -0.0147 0.9194 0.0186 -2.750 -0.1725 0.00809 0.00234 -0.0141 0.9064 0.0213 -2.500 -0.1462 0.00788 0.00211 -0.0135 0.8924 0.0267 -2.250 -0.1206 0.00755 0.00189 -0.0129 0.8771 0.0602 -2.000 -0.0959 0.00707 0.00169 -0.0123 0.8595 0.1496 -1.750 -0.0729 0.00636 0.00148 -0.0116 0.8412 0.3127 -1.500 -0.0510 0.00557 0.00130 -0.0107 0.8212 0.5079 -1.250 -0.0274 0.00513 0.00121 -0.0098 0.7978 0.6322 -1.000 -0.0031 0.00488 0.00116 -0.0089 0.7733 0.7192 -0.750 0.0210 0.00474 0.00116 -0.0079 0.7450 0.7918 -0.500 0.0457 0.00472 0.00117 -0.0069 0.7117 0.8396 -0.250 0.0702 0.00477 0.00121 -0.0059 0.6755 0.8783 0.000 0.0948 0.00490 0.00124 -0.0049 0.6363 0.9031 0.250 0.1196 0.00509 0.00129 -0.0039 0.5900 0.9208 0.500 0.1443 0.00533 0.00134 -0.0031 0.5364 0.9340 0.750 0.1693 0.00558 0.00139 -0.0024 0.4859 0.9451 1.000 0.1948 0.00585 0.00146 -0.0018 0.4354 0.9540 1.250 0.2214 0.00611 0.00153 -0.0015 0.3886 0.9613 1.500 0.2493 0.00634 0.00161 -0.0014 0.3527 0.9679 1.750 0.2779 0.00655 0.00168 -0.0016 0.3236 0.9737 2.000 0.3104 0.00677 0.00177 -0.0027 0.2969 0.9771 2.250 0.3429 0.00696 0.00185 -0.0037 0.2764 0.9807 2.500 0.3741 0.00713 0.00194 -0.0045 0.2604 0.9846 2.750 0.4099 0.00730 0.00203 -0.0063 0.2456 0.9857 3.000 0.4455 0.00747 0.00213 -0.0081 0.2324 0.9870 3.250 0.4805 0.00763 0.00222 -0.0098 0.2216 0.9887 3.500 0.5146 0.00779 0.00232 -0.0113 0.2114 0.9906 3.750 0.5480 0.00792 0.00243 -0.0126 0.2031 0.9927 4.000 0.5810 0.00809 0.00255 -0.0138 0.1938 0.9947 4.250 0.6158 0.00822 0.00264 -0.0155 0.1861 0.9958 4.500 0.6500 0.00838 0.00277 -0.0170 0.1787 0.9971 4.750 0.6842 0.00852 0.00289 -0.0185 0.1721 0.9986 5.000 0.7180 0.00870 0.00303 -0.0200 0.1647 0.9998 5.250 0.7428 0.00882 0.00315 -0.0195 0.1595 1.0000 5.500 0.7657 0.00899 0.00329 -0.0186 0.1534 1.0000 5.750 0.7890 0.00912 0.00343 -0.0177 0.1494 1.0000 6.000 0.8121 0.00927 0.00357 -0.0169 0.1448 1.0000 6.250 0.8348 0.00948 0.00376 -0.0159 0.1392 1.0000 6.500 0.8581 0.00963 0.00392 -0.0151 0.1355 1.0000 6.750 0.8814 0.00980 0.00408 -0.0142 0.1303 1.0000 7.000 0.9041 0.01005 0.00431 -0.0133 0.1242 1.0000 7.250 0.9281 0.01019 0.00448 -0.0126 0.1210 1.0000 7.500 0.9516 0.01040 0.00468 -0.0118 0.1166 1.0000 7.750 0.9748 0.01067 0.00494 -0.0110 0.1110 1.0000 8.000 0.9991 0.01083 0.00513 -0.0104 0.1077 1.0000 8.250 1.0229 0.01107 0.00536 -0.0098 0.1031 1.0000 8.500 1.0466 0.01136 0.00565 -0.0091 0.0983 1.0000 8.750 1.0713 0.01155 0.00588 -0.0087 0.0954 1.0000 9.000 1.0956 0.01183 0.00615 -0.0081 0.0907 1.0000 9.250 1.1197 0.01213 0.00646 -0.0076 0.0859 1.0000 9.500 1.1444 0.01238 0.00674 -0.0072 0.0817 1.0000 9.750 1.1680 0.01277 0.00710 -0.0067 0.0751 1.0000 10.000 1.1924 0.01306 0.00742 -0.0063 0.0698 1.0000 10.250 1.2156 0.01349 0.00782 -0.0057 0.0622 1.0000 10.500 1.2378 0.01403 0.00831 -0.0051 0.0520 1.0000 10.750 1.2586 0.01472 0.00893 -0.0043 0.0410 1.0000 11.000 1.2793 0.01540 0.00959 -0.0034 0.0341 1.0000 11.250 1.2999 0.01609 0.01029 -0.0025 0.0295 1.0000 11.500 1.3207 0.01671 0.01094 -0.0017 0.0265 1.0000 11.750 1.3404 0.01744 0.01171 -0.0008 0.0236 1.0000 12.000 1.3613 0.01799 0.01232 0.0000 0.0218 1.0000 12.250 1.3795 0.01880 0.01315 0.0011 0.0197 1.0000 12.500 1.3985 0.01948 0.01391 0.0021 0.0184 1.0000 12.750 1.4175 0.02011 0.01460 0.0031 0.0173 1.0000 13.000 1.4343 0.02090 0.01544 0.0043 0.0161 1.0000 13.250 1.4463 0.02204 0.01666 0.0061 0.0148 1.0000 13.500 1.4629 0.02270 0.01741 0.0073 0.0143 1.0000 13.750 1.4761 0.02346 0.01825 0.0090 0.0136 1.0000 14.000 1.4860 0.02434 0.01920 0.0112 0.0130 1.0000 14.250 1.4928 0.02546 0.02039 0.0134 0.0123 1.0000 14.500 1.4921 0.02716 0.02220 0.0161 0.0115 1.0000 14.750 1.4988 0.02843 0.02356 0.0177 0.0112 1.0000 15.000 1.5056 0.02977 0.02501 0.0191 0.0109 1.0000 15.250 1.5096 0.03144 0.02678 0.0203 0.0105 1.0000 15.500 1.5116 0.03342 0.02886 0.0211 0.0101 1.0000 15.750 1.5109 0.03586 0.03142 0.0215 0.0098 1.0000 16.000 1.5064 0.03896 0.03464 0.0213 0.0096 1.0000 16.250 1.4972 0.04303 0.03885 0.0202 0.0093 1.0000 16.500 1.4821 0.04841 0.04438 0.0178 0.0092 1.0000 16.750 1.4611 0.05542 0.05158 0.0139 0.0091 1.0000 17.000 1.4341 0.06400 0.06035 0.0089 0.0092 1.0000 17.250 1.3993 0.07411 0.07066 0.0035 0.0093 1.0000 17.500 1.3558 0.08534 0.08209 -0.0020 0.0096 1.0000 17.750 1.3068 0.09729 0.09422 -0.0077 0.0099 1.0000