XFOIL Version 6.96 Calculated polar for: USA 48 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5334 0.07998 0.07525 -0.0611 1.0000 0.0969 -10.000 -0.5171 0.07933 0.07464 -0.0575 1.0000 0.0985 -9.750 -0.6152 0.06818 0.06344 -0.0606 1.0000 0.0864 -9.500 -0.7076 0.06459 0.05949 -0.0534 1.0000 0.0841 -9.250 -0.7025 0.06096 0.05586 -0.0515 1.0000 0.0813 -9.000 -0.7170 0.05732 0.05211 -0.0484 1.0000 0.0796 -8.750 -0.7362 0.05330 0.04779 -0.0449 1.0000 0.0774 -8.500 -0.7689 0.04798 0.04154 -0.0396 1.0000 0.0734 -8.250 -0.7682 0.04515 0.03840 -0.0369 1.0000 0.0735 -8.000 -0.7597 0.04291 0.03608 -0.0349 1.0000 0.0748 -7.750 -0.7526 0.04075 0.03368 -0.0326 1.0000 0.0757 -7.500 -0.7449 0.03840 0.03097 -0.0302 1.0000 0.0760 -7.250 -0.7344 0.03632 0.02855 -0.0281 1.0000 0.0764 -7.000 -0.7218 0.03475 0.02674 -0.0261 1.0000 0.0781 -6.750 -0.7086 0.03340 0.02510 -0.0242 1.0000 0.0805 -6.500 -0.6941 0.03214 0.02350 -0.0223 1.0000 0.0825 -6.250 -0.6590 0.03043 0.02166 -0.0242 0.9952 0.0856 -6.000 -0.6202 0.02945 0.02061 -0.0268 0.9881 0.0912 -5.750 -0.5801 0.02872 0.01958 -0.0293 0.9813 0.0956 -5.500 -0.5446 0.02741 0.01846 -0.0313 0.9742 0.1021 -5.250 -0.5090 0.02672 0.01764 -0.0330 0.9664 0.1087 -5.000 -0.4735 0.02568 0.01677 -0.0350 0.9596 0.1184 -4.750 -0.4452 0.02481 0.01596 -0.0355 0.9505 0.1289 -4.500 -0.4084 0.02387 0.01536 -0.0378 0.9442 0.1593 -4.250 -0.3853 0.02293 0.01511 -0.0375 0.9341 0.2815 -4.000 -0.3537 0.02285 0.01512 -0.0385 0.9253 0.3483 -3.750 -0.3175 0.02283 0.01508 -0.0402 0.9174 0.3912 -3.500 -0.2897 0.02274 0.01497 -0.0404 0.9077 0.4188 -3.250 -0.2499 0.02251 0.01478 -0.0427 0.9013 0.4480 -3.000 -0.2253 0.02231 0.01468 -0.0422 0.8909 0.4769 -2.750 -0.1854 0.02194 0.01450 -0.0442 0.8852 0.5197 -2.500 -0.1647 0.02187 0.01469 -0.0427 0.8743 0.5588 -2.250 -0.1242 0.02180 0.01481 -0.0443 0.8691 0.6172 -2.000 -0.1058 0.02204 0.01507 -0.0421 0.8574 0.6662 -1.750 -0.0661 0.02192 0.01495 -0.0432 0.8530 0.7160 -1.500 -0.0513 0.02202 0.01509 -0.0402 0.8413 0.7508 -1.250 -0.0108 0.02158 0.01468 -0.0411 0.8375 0.7925 -1.000 0.0059 0.02162 0.01478 -0.0383 0.8261 0.8246 -0.750 0.0548 0.02116 0.01431 -0.0408 0.8228 0.8565 -0.500 0.0901 0.02126 0.01442 -0.0415 0.8135 0.8826 -0.250 0.1523 0.02099 0.01407 -0.0468 0.8095 0.9058 0.000 0.2296 0.02060 0.01357 -0.0551 0.8070 0.9216 0.250 0.2930 0.02056 0.01346 -0.0614 0.7986 0.9341 0.500 0.3821 0.02013 0.01291 -0.0722 0.7936 0.9442 0.750 0.4694 0.01971 0.01240 -0.0829 0.7875 0.9572 1.000 0.5332 0.01940 0.01202 -0.0896 0.7769 0.9692 1.250 0.5913 0.01902 0.01157 -0.0954 0.7638 0.9776 1.500 0.6436 0.01865 0.01113 -0.1001 0.7498 0.9858 1.750 0.6918 0.01838 0.01078 -0.1042 0.7358 0.9935 2.000 0.7378 0.01813 0.01046 -0.1080 0.7221 1.0000 2.250 0.7602 0.01809 0.01035 -0.1072 0.7100 1.0000 2.500 0.7710 0.01825 0.01052 -0.1044 0.6972 1.0000 2.750 0.7845 0.01833 0.01058 -0.1020 0.6843 1.0000 3.000 0.8000 0.01837 0.01060 -0.0999 0.6721 1.0000 3.250 0.8192 0.01837 0.01054 -0.0985 0.6611 1.0000 3.500 0.8230 0.01852 0.01073 -0.0944 0.6486 1.0000 3.750 0.8289 0.01864 0.01085 -0.0907 0.6373 1.0000 4.000 0.8434 0.01868 0.01084 -0.0884 0.6271 1.0000 4.250 0.8516 0.01884 0.01099 -0.0850 0.6156 1.0000 4.500 0.8647 0.01904 0.01118 -0.0823 0.6037 1.0000 4.750 0.8846 0.01920 0.01130 -0.0808 0.5924 1.0000 5.000 0.9086 0.01932 0.01136 -0.0799 0.5813 1.0000 5.250 0.9234 0.01957 0.01163 -0.0774 0.5682 1.0000 5.500 0.9410 0.01980 0.01185 -0.0754 0.5552 1.0000 5.750 0.9615 0.02004 0.01207 -0.0739 0.5430 1.0000 6.000 0.9861 0.02026 0.01225 -0.0732 0.5316 1.0000 6.250 1.0045 0.02051 0.01251 -0.0713 0.5184 1.0000 6.500 1.0206 0.02079 0.01283 -0.0691 0.5048 1.0000 6.750 1.0380 0.02110 0.01317 -0.0671 0.4918 1.0000 7.000 1.0575 0.02141 0.01349 -0.0655 0.4796 1.0000 7.250 1.0787 0.02168 0.01375 -0.0641 0.4673 1.0000 7.500 1.0956 0.02198 0.01410 -0.0621 0.4543 1.0000 7.750 1.1097 0.02233 0.01453 -0.0595 0.4408 1.0000 8.000 1.1244 0.02267 0.01493 -0.0571 0.4272 1.0000 8.250 1.1381 0.02297 0.01526 -0.0545 0.4124 1.0000 8.500 1.1490 0.02325 0.01554 -0.0513 0.3959 1.0000 8.750 1.1576 0.02355 0.01581 -0.0478 0.3783 1.0000 9.000 1.1640 0.02391 0.01609 -0.0440 0.3599 1.0000 9.250 1.1659 0.02439 0.01654 -0.0395 0.3417 1.0000 9.500 1.1680 0.02500 0.01713 -0.0353 0.3236 1.0000 9.750 1.1709 0.02570 0.01780 -0.0314 0.3058 1.0000 10.000 1.1744 0.02648 0.01856 -0.0278 0.2891 1.0000 10.250 1.1784 0.02731 0.01938 -0.0245 0.2738 1.0000 10.500 1.1836 0.02820 0.02029 -0.0215 0.2603 1.0000 10.750 1.1885 0.02913 0.02122 -0.0187 0.2480 1.0000 11.000 1.1920 0.03012 0.02221 -0.0159 0.2364 1.0000 11.250 1.1928 0.03125 0.02344 -0.0130 0.2235 1.0000 11.500 1.1947 0.03247 0.02475 -0.0105 0.2115 1.0000 11.750 1.1943 0.03388 0.02623 -0.0080 0.1986 1.0000 12.000 1.1920 0.03555 0.02796 -0.0057 0.1847 1.0000 12.250 1.1856 0.03766 0.03008 -0.0035 0.1685 1.0000 12.500 1.1752 0.04032 0.03266 -0.0016 0.1515 1.0000 12.750 1.1634 0.04338 0.03563 0.0001 0.1365 1.0000 13.000 1.1503 0.04680 0.03895 0.0015 0.1219 1.0000 13.250 1.1394 0.05026 0.04243 0.0025 0.1083 1.0000 13.500 1.1316 0.05367 0.04592 0.0031 0.0955 1.0000 13.750 1.1277 0.05685 0.04919 0.0034 0.0844 1.0000 14.000 1.1247 0.05998 0.05237 0.0035 0.0773 1.0000 14.250 1.1183 0.06361 0.05595 0.0033 0.0727 1.0000 14.500 1.1168 0.06665 0.05903 0.0034 0.0691 1.0000 14.750 1.1151 0.06976 0.06215 0.0034 0.0661 1.0000 15.000 1.1152 0.07249 0.06479 0.0038 0.0633 1.0000 15.250 1.1217 0.07454 0.06690 0.0045 0.0607 1.0000 15.500 1.1279 0.07672 0.06913 0.0051 0.0580 1.0000 15.750 1.1395 0.07814 0.07047 0.0062 0.0554 1.0000 16.000 1.1650 0.07836 0.07064 0.0086 0.0532 1.0000 16.250 1.1708 0.08108 0.07358 0.0089 0.0524 1.0000 16.500 1.1722 0.08438 0.07711 0.0087 0.0515 1.0000 16.750 1.1699 0.08816 0.08112 0.0082 0.0506 1.0000 17.000 1.1649 0.09229 0.08547 0.0074 0.0498 1.0000 17.250 1.1573 0.09687 0.09025 0.0061 0.0490 1.0000 17.500 1.1460 0.10207 0.09568 0.0043 0.0489 1.0000 17.750 1.1307 0.10803 0.10187 0.0019 0.0486 1.0000 18.000 1.1071 0.11559 0.10971 -0.0019 0.0491 1.0000 18.250 1.0760 0.12493 0.11932 -0.0072 0.0495 1.0000 18.500 1.0318 0.13783 0.13250 -0.0152 0.0511 1.0000