XFOIL Version 6.96 Calculated polar for: 74-130 WP2 MOD 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.1688 0.08757 0.08422 -0.0964 0.7965 0.0098 -9.750 -0.1659 0.08407 0.08073 -0.0982 0.7954 0.0104 -9.500 -0.1655 0.08012 0.07680 -0.1000 0.7943 0.0092 -9.250 -0.1633 0.07674 0.07343 -0.1018 0.7932 0.0099 -9.000 -0.1600 0.07214 0.06884 -0.1057 0.7917 0.0119 -8.750 -0.1612 0.06784 0.06458 -0.1087 0.7902 0.0119 -8.500 -0.1665 0.06306 0.05982 -0.1128 0.7885 0.0120 -8.000 -0.1968 0.05625 0.05300 -0.1127 0.7840 0.0099 -6.750 -0.1887 0.03439 0.03017 -0.1091 0.7716 0.0076 -6.500 -0.1797 0.03094 0.02644 -0.1079 0.7697 0.0074 -6.250 -0.1665 0.02764 0.02284 -0.1066 0.7681 0.0072 -6.000 -0.1503 0.02457 0.01939 -0.1053 0.7667 0.0070 -5.750 -0.1318 0.02155 0.01596 -0.1040 0.7653 0.0069 -5.500 -0.1101 0.01929 0.01334 -0.1032 0.7640 0.0067 -5.250 -0.0868 0.01738 0.01113 -0.1025 0.7624 0.0068 -5.000 -0.0622 0.01595 0.00945 -0.1019 0.7606 0.0069 -4.750 -0.0370 0.01486 0.00819 -0.1015 0.7588 0.0071 -4.500 -0.0116 0.01402 0.00723 -0.1012 0.7570 0.0074 -4.250 0.0143 0.01340 0.00648 -0.1010 0.7554 0.0077 -4.000 0.0391 0.01262 0.00561 -0.1007 0.7538 0.0081 -3.750 0.0645 0.01203 0.00496 -0.1005 0.7522 0.0087 -3.500 0.0910 0.01167 0.00456 -0.1005 0.7507 0.0094 -3.250 0.1174 0.01139 0.00428 -0.1005 0.7486 0.0104 -3.000 0.1439 0.01109 0.00394 -0.1004 0.7462 0.0112 -2.750 0.1706 0.01077 0.00357 -0.1004 0.7439 0.0117 -2.500 0.1977 0.01049 0.00323 -0.1005 0.7418 0.0126 -2.250 0.2250 0.01023 0.00294 -0.1005 0.7398 0.0168 -2.000 0.2524 0.00997 0.00273 -0.1007 0.7380 0.0386 -1.750 0.2788 0.00956 0.00256 -0.1009 0.7359 0.1184 -1.500 0.3001 0.00798 0.00237 -0.1012 0.7330 0.5275 -1.250 0.3223 0.00746 0.00262 -0.1001 0.7301 0.7519 -1.000 0.3497 0.00759 0.00272 -0.0999 0.7272 0.7914 -0.750 0.3759 0.00773 0.00284 -0.0994 0.7247 0.8117 -0.500 0.4029 0.00782 0.00290 -0.0992 0.7220 0.8229 -0.250 0.4300 0.00788 0.00295 -0.0991 0.7184 0.8304 0.000 0.4574 0.00789 0.00294 -0.0991 0.7148 0.8354 0.250 0.4850 0.00789 0.00291 -0.0991 0.7117 0.8387 0.500 0.5132 0.00789 0.00288 -0.0994 0.7084 0.8413 0.750 0.5414 0.00790 0.00288 -0.0997 0.7039 0.8434 1.000 0.5699 0.00790 0.00285 -0.1001 0.6996 0.8453 1.250 0.5986 0.00789 0.00281 -0.1005 0.6955 0.8469 1.500 0.6264 0.00789 0.00282 -0.1007 0.6899 0.8479 1.750 0.6542 0.00788 0.00281 -0.1009 0.6847 0.8490 2.000 0.6820 0.00789 0.00282 -0.1012 0.6794 0.8501 2.250 0.7098 0.00790 0.00283 -0.1014 0.6734 0.8510 2.500 0.7376 0.00793 0.00284 -0.1016 0.6679 0.8521 2.750 0.7651 0.00796 0.00290 -0.1018 0.6614 0.8533 3.000 0.7926 0.00801 0.00293 -0.1020 0.6555 0.8544 3.250 0.8201 0.00806 0.00300 -0.1022 0.6486 0.8554 3.750 0.8746 0.00821 0.00317 -0.1026 0.6358 0.8574 4.000 0.9012 0.00831 0.00326 -0.1026 0.6284 0.8586 4.250 0.9270 0.00844 0.00337 -0.1025 0.6162 0.8598 4.500 0.9514 0.00863 0.00350 -0.1021 0.5996 0.8609 4.750 0.9747 0.00882 0.00366 -0.1014 0.5808 0.8618 5.000 0.9970 0.00906 0.00386 -0.1006 0.5613 0.8629 5.250 1.0196 0.00930 0.00407 -0.0999 0.5440 0.8639 5.500 1.0394 0.00962 0.00432 -0.0987 0.5164 0.8652 5.750 1.0555 0.01007 0.00463 -0.0968 0.4738 0.8667 6.000 1.0633 0.01084 0.00512 -0.0935 0.4068 0.8689 6.250 1.0624 0.01194 0.00588 -0.0888 0.3374 0.8715 6.500 1.0628 0.01281 0.00653 -0.0842 0.2879 0.8739 6.750 1.0618 0.01381 0.00731 -0.0797 0.2386 0.8763 7.000 1.0614 0.01489 0.00818 -0.0756 0.1918 0.8790 7.250 1.0642 0.01596 0.00909 -0.0722 0.1528 0.8819 7.500 1.0693 0.01702 0.01001 -0.0694 0.1197 0.8848 7.750 1.0761 0.01808 0.01095 -0.0670 0.0921 0.8878 8.000 1.0831 0.01914 0.01192 -0.0646 0.0676 0.8911 8.250 1.0912 0.02017 0.01290 -0.0625 0.0486 0.8950 8.500 1.1011 0.02115 0.01384 -0.0606 0.0359 0.8990 9.000 1.1229 0.02298 0.01569 -0.0572 0.0211 0.9086 9.250 1.1343 0.02387 0.01662 -0.0557 0.0171 0.9157 9.500 1.1459 0.02473 0.01754 -0.0540 0.0143 0.9262 10.000 1.1723 0.02669 0.01963 -0.0521 0.0088 1.0000 10.250 1.1837 0.02784 0.02081 -0.0509 0.0069 1.0000 10.500 1.1943 0.02908 0.02212 -0.0497 0.0059 1.0000 10.750 1.2058 0.03027 0.02339 -0.0486 0.0054 1.0000 11.000 1.2165 0.03153 0.02473 -0.0474 0.0050 1.0000 11.250 1.2266 0.03286 0.02614 -0.0463 0.0046 1.0000 11.500 1.2352 0.03435 0.02770 -0.0451 0.0042 1.0000 11.750 1.2424 0.03600 0.02943 -0.0438 0.0039 1.0000 12.000 1.2485 0.03780 0.03132 -0.0426 0.0037 1.0000 12.250 1.2535 0.03976 0.03339 -0.0413 0.0036 1.0000 12.500 1.2613 0.04149 0.03522 -0.0404 0.0035 1.0000 12.750 1.2693 0.04324 0.03708 -0.0395 0.0035 1.0000 13.000 1.2771 0.04506 0.03903 -0.0387 0.0033 1.0000 13.250 1.2830 0.04712 0.04121 -0.0379 0.0032 1.0000 13.500 1.2906 0.04906 0.04325 -0.0373 0.0030 1.0000 13.750 1.2957 0.05129 0.04560 -0.0367 0.0029 1.0000 14.000 1.3010 0.05357 0.04799 -0.0362 0.0028 1.0000 14.250 1.3055 0.05600 0.05055 -0.0357 0.0028 1.0000 14.500 1.3088 0.05863 0.05332 -0.0353 0.0027 1.0000 14.750 1.3114 0.06140 0.05623 -0.0350 0.0027 1.0000 15.000 1.3136 0.06430 0.05926 -0.0349 0.0026 1.0000 15.250 1.3149 0.06740 0.06250 -0.0349 0.0026 1.0000 15.500 1.3152 0.07070 0.06594 -0.0351 0.0025 1.0000 15.750 1.3142 0.07424 0.06964 -0.0354 0.0025 1.0000 16.000 1.3121 0.07805 0.07361 -0.0359 0.0024 1.0000 16.250 1.3093 0.08206 0.07776 -0.0367 0.0024 1.0000 16.500 1.3050 0.08640 0.08227 -0.0377 0.0023 1.0000 16.750 1.2987 0.09118 0.08724 -0.0389 0.0023 1.0000 17.000 1.2923 0.09610 0.09231 -0.0405 0.0023 1.0000 17.250 1.2836 0.10156 0.09795 -0.0424 0.0023 1.0000 17.500 1.2739 0.10741 0.10397 -0.0448 0.0022 1.0000 17.750 1.2630 0.11367 0.11041 -0.0475 0.0022 1.0000 18.000 1.2509 0.12039 0.11730 -0.0508 0.0022 1.0000 18.250 1.2378 0.12760 0.12469 -0.0545 0.0022 1.0000 18.500 1.2249 0.13509 0.13234 -0.0588 0.0022 1.0000 18.750 1.2097 0.14339 0.14082 -0.0636 0.0022 1.0000 19.000 1.1943 0.15215 0.14975 -0.0690 0.0022 1.0000