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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5909 0.07536 0.07176 -0.0253 1.0000 0.0156 -9.000 -0.5995 0.07102 0.06737 -0.0277 1.0000 0.0155 -8.750 -0.6105 0.06710 0.06339 -0.0282 1.0000 0.0153 -8.500 -0.6176 0.06300 0.05920 -0.0283 1.0000 0.0151 -8.250 -0.6222 0.05878 0.05484 -0.0280 1.0000 0.0149 -8.000 -0.6247 0.05448 0.05036 -0.0271 1.0000 0.0147 -7.750 -0.6253 0.05013 0.04579 -0.0257 1.0000 0.0144 -7.500 -0.6243 0.04575 0.04113 -0.0236 1.0000 0.0141 -7.250 -0.6218 0.04139 0.03644 -0.0211 1.0000 0.0138 -7.000 -0.6176 0.03720 0.03185 -0.0181 1.0000 0.0136 -6.750 -0.6099 0.03360 0.02784 -0.0152 1.0000 0.0135 -6.500 -0.5991 0.03054 0.02438 -0.0125 1.0000 0.0136 -6.250 -0.5856 0.02799 0.02145 -0.0101 1.0000 0.0137 -6.000 -0.5698 0.02581 0.01890 -0.0079 1.0000 0.0140 -5.750 -0.5523 0.02395 0.01672 -0.0059 1.0000 0.0143 -5.500 -0.5333 0.02243 0.01490 -0.0041 1.0000 0.0150 -5.250 -0.5135 0.02119 0.01337 -0.0024 1.0000 0.0159 -5.000 -0.4939 0.02027 0.01242 -0.0011 1.0000 0.0166 -4.750 -0.4714 0.01932 0.01136 -0.0002 0.9995 0.0172 -4.500 -0.4382 0.01819 0.01013 -0.0013 0.9964 0.0179 -4.250 -0.4050 0.01719 0.00903 -0.0024 0.9932 0.0188 -4.000 -0.3721 0.01633 0.00808 -0.0035 0.9890 0.0198 -3.750 -0.3384 0.01551 0.00729 -0.0050 0.9854 0.0214 -3.500 -0.3055 0.01499 0.00675 -0.0062 0.9803 0.0242 -3.250 -0.2712 0.01434 0.00608 -0.0077 0.9754 0.0271 -3.000 -0.2355 0.01384 0.00553 -0.0093 0.9707 0.0312 -2.750 -0.2018 0.01333 0.00504 -0.0106 0.9636 0.0403 -2.500 -0.1654 0.01266 0.00451 -0.0123 0.9538 0.0691 -2.250 -0.1335 0.01153 0.00402 -0.0135 0.9383 0.2161 -2.000 -0.1125 0.00989 0.00367 -0.0127 0.9218 0.5265 -1.750 -0.0914 0.00909 0.00369 -0.0105 0.9078 0.7277 -1.500 -0.0648 0.00892 0.00377 -0.0090 0.8943 0.8209 -1.250 -0.0350 0.00901 0.00396 -0.0078 0.8795 0.8881 -1.000 -0.0025 0.00913 0.00400 -0.0078 0.8619 0.9170 -0.750 0.0294 0.00916 0.00390 -0.0080 0.8409 0.9302 -0.500 0.0624 0.00919 0.00379 -0.0086 0.8169 0.9392 -0.250 0.0949 0.00923 0.00367 -0.0092 0.7883 0.9470 0.000 0.1273 0.00931 0.00356 -0.0097 0.7548 0.9544 0.250 0.1594 0.00942 0.00346 -0.0103 0.7152 0.9608 0.500 0.1936 0.00958 0.00336 -0.0114 0.6675 0.9659 0.750 0.2239 0.00980 0.00330 -0.0118 0.6141 0.9726 1.000 0.2585 0.01008 0.00325 -0.0133 0.5525 0.9764 1.250 0.2908 0.01041 0.00325 -0.0144 0.4902 0.9817 1.500 0.3235 0.01074 0.00328 -0.0156 0.4349 0.9863 1.750 0.3574 0.01105 0.00333 -0.0172 0.3888 0.9904 2.000 0.3906 0.01133 0.00341 -0.0186 0.3524 0.9947 2.250 0.4252 0.01157 0.00348 -0.0204 0.3242 0.9982 2.500 0.4538 0.01180 0.00357 -0.0208 0.3025 1.0000 2.750 0.4767 0.01200 0.00367 -0.0200 0.2856 1.0000 3.000 0.4995 0.01219 0.00378 -0.0192 0.2714 1.0000 3.250 0.5224 0.01238 0.00391 -0.0184 0.2590 1.0000 3.500 0.5452 0.01258 0.00406 -0.0176 0.2476 1.0000 3.750 0.5679 0.01281 0.00423 -0.0167 0.2376 1.0000 4.000 0.5907 0.01302 0.00441 -0.0158 0.2285 1.0000 4.250 0.6134 0.01325 0.00461 -0.0149 0.2205 1.0000 4.500 0.6361 0.01349 0.00484 -0.0141 0.2122 1.0000 4.750 0.6590 0.01373 0.00507 -0.0132 0.2047 1.0000 5.000 0.6817 0.01399 0.00531 -0.0123 0.1976 1.0000 5.250 0.7046 0.01426 0.00558 -0.0114 0.1916 1.0000 5.500 0.7276 0.01453 0.00587 -0.0106 0.1851 1.0000 5.750 0.7501 0.01485 0.00616 -0.0097 0.1793 1.0000 6.000 0.7733 0.01512 0.00648 -0.0089 0.1731 1.0000 6.250 0.7960 0.01545 0.00681 -0.0080 0.1677 1.0000 6.500 0.8190 0.01579 0.00718 -0.0072 0.1631 1.0000 6.750 0.8423 0.01611 0.00756 -0.0065 0.1579 1.0000 7.000 0.8649 0.01649 0.00793 -0.0057 0.1529 1.0000 7.250 0.8883 0.01685 0.00837 -0.0050 0.1482 1.0000 7.500 0.9116 0.01722 0.00881 -0.0043 0.1437 1.0000 7.750 0.9344 0.01766 0.00926 -0.0036 0.1397 1.0000 8.000 0.9573 0.01810 0.00978 -0.0029 0.1358 1.0000 8.250 0.9807 0.01847 0.01026 -0.0022 0.1306 1.0000 8.500 1.0030 0.01890 0.01069 -0.0015 0.1253 1.0000 8.750 1.0263 0.01928 0.01119 -0.0009 0.1197 1.0000 9.000 1.0489 0.01969 0.01168 -0.0003 0.1143 1.0000 9.250 1.0708 0.02018 0.01223 0.0005 0.1097 1.0000 9.500 1.0935 0.02060 0.01279 0.0011 0.1043 1.0000 9.750 1.1144 0.02113 0.01333 0.0019 0.0990 1.0000 10.000 1.1367 0.02159 0.01397 0.0025 0.0932 1.0000 10.250 1.1571 0.02215 0.01456 0.0034 0.0872 1.0000 10.500 1.1783 0.02269 0.01526 0.0041 0.0808 1.0000 10.750 1.1975 0.02334 0.01596 0.0050 0.0743 1.0000 11.000 1.2169 0.02402 0.01675 0.0059 0.0666 1.0000 11.250 1.2345 0.02483 0.01766 0.0070 0.0593 1.0000 11.500 1.2500 0.02579 0.01867 0.0083 0.0523 1.0000 11.750 1.2635 0.02689 0.01982 0.0097 0.0460 1.0000 12.000 1.2757 0.02803 0.02107 0.0113 0.0413 1.0000 12.250 1.2834 0.02938 0.02249 0.0134 0.0377 1.0000 12.500 1.2892 0.03068 0.02393 0.0157 0.0351 1.0000 12.750 1.2931 0.03217 0.02557 0.0179 0.0328 1.0000 13.000 1.2931 0.03402 0.02752 0.0199 0.0310 1.0000 13.250 1.2911 0.03616 0.02979 0.0216 0.0297 1.0000 13.500 1.2906 0.03838 0.03220 0.0227 0.0284 1.0000 13.750 1.2873 0.04107 0.03507 0.0232 0.0273 1.0000 14.000 1.2814 0.04434 0.03852 0.0229 0.0264 1.0000 14.250 1.2724 0.04841 0.04275 0.0217 0.0257 1.0000 14.500 1.2596 0.05350 0.04802 0.0193 0.0251 1.0000 14.750 1.2434 0.05972 0.05442 0.0157 0.0248 1.0000 15.000 1.2241 0.06694 0.06181 0.0114 0.0246 1.0000 15.250 1.2025 0.07475 0.06979 0.0070 0.0246 1.0000 15.500 1.1796 0.08274 0.07794 0.0027 0.0246 1.0000 15.750 1.1564 0.09068 0.08601 -0.0014 0.0246 1.0000