XFOIL Version 6.96 Calculated polar for: NACA 64(3)-618 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 ------ -------- --------- --------- -------- -------- -------- -15.500 -0.6575 0.07640 0.07165 -0.0875 1.0000 0.0286 -15.250 -0.6865 0.06914 0.06417 -0.0916 1.0000 0.0288 -15.000 -0.7091 0.06351 0.05833 -0.0942 1.0000 0.0289 -14.750 -0.7272 0.05895 0.05359 -0.0957 1.0000 0.0291 -14.500 -0.7434 0.05498 0.04941 -0.0967 1.0000 0.0295 -14.250 -0.7562 0.05165 0.04590 -0.0970 1.0000 0.0297 -14.000 -0.7680 0.04870 0.04276 -0.0967 1.0000 0.0300 -13.750 -0.7823 0.04603 0.03987 -0.0958 1.0000 0.0304 -13.500 -0.7823 0.04439 0.03821 -0.0947 0.9993 0.0306 -13.250 -0.7628 0.04234 0.03613 -0.0971 0.9888 0.0311 -13.000 -0.7441 0.04039 0.03408 -0.0996 0.9794 0.0316 -12.750 -0.7235 0.03843 0.03199 -0.1023 0.9707 0.0322 -12.500 -0.7021 0.03656 0.02996 -0.1048 0.9612 0.0330 -12.250 -0.6793 0.03473 0.02792 -0.1073 0.9519 0.0340 -12.000 -0.6545 0.03297 0.02589 -0.1099 0.9425 0.0349 -11.750 -0.6271 0.03166 0.02456 -0.1118 0.9329 0.0357 -11.250 -0.5737 0.02932 0.02207 -0.1155 0.9125 0.0374 -11.000 -0.5498 0.02825 0.02087 -0.1165 0.9019 0.0386 -10.750 -0.5272 0.02729 0.01973 -0.1171 0.8911 0.0397 -10.500 -0.5078 0.02639 0.01876 -0.1169 0.8801 0.0406 -10.000 -0.4729 0.02480 0.01708 -0.1158 0.8594 0.0422 -9.750 -0.4564 0.02406 0.01625 -0.1150 0.8501 0.0435 -9.500 -0.4419 0.02338 0.01548 -0.1138 0.8400 0.0447 -9.250 -0.4262 0.02273 0.01470 -0.1126 0.8316 0.0459 -9.000 -0.4163 0.02202 0.01399 -0.1108 0.8220 0.0471 -8.750 -0.4036 0.02143 0.01332 -0.1093 0.8141 0.0483 -8.500 -0.3894 0.02084 0.01269 -0.1081 0.8053 0.0498 -8.250 -0.3727 0.02027 0.01202 -0.1070 0.7979 0.0514 -8.000 -0.3563 0.01969 0.01140 -0.1059 0.7903 0.0533 -7.750 -0.3387 0.01915 0.01083 -0.1050 0.7828 0.0556 -7.500 -0.3187 0.01868 0.01025 -0.1043 0.7766 0.0585 -7.250 -0.2998 0.01816 0.00972 -0.1035 0.7690 0.0615 -7.000 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0.2142 0.01317 0.00549 -0.1036 0.6584 0.5832 -2.000 0.2425 0.01318 0.00545 -0.1037 0.6541 0.5867 -1.750 0.2715 0.01320 0.00539 -0.1040 0.6504 0.5908 -1.500 0.2999 0.01321 0.00538 -0.1043 0.6459 0.5949 -1.250 0.3287 0.01322 0.00532 -0.1047 0.6414 0.5989 -1.000 0.3572 0.01323 0.00530 -0.1049 0.6374 0.6018 -0.750 0.3859 0.01326 0.00528 -0.1051 0.6340 0.6044 -0.500 0.4143 0.01330 0.00530 -0.1053 0.6304 0.6076 -0.250 0.4425 0.01334 0.00535 -0.1055 0.6263 0.6115 0.000 0.4711 0.01339 0.00537 -0.1058 0.6224 0.6154 0.250 0.5002 0.01343 0.00536 -0.1063 0.6187 0.6192 0.500 0.5287 0.01348 0.00539 -0.1064 0.6155 0.6220 0.750 0.5564 0.01355 0.00550 -0.1066 0.6119 0.6253 1.000 0.5843 0.01363 0.00561 -0.1067 0.6083 0.6290 1.250 0.6126 0.01371 0.00569 -0.1070 0.6049 0.6332 1.500 0.6415 0.01380 0.00576 -0.1074 0.6019 0.6377 1.750 0.6698 0.01389 0.00587 -0.1076 0.5992 0.6414 2.000 0.6984 0.01400 0.00599 -0.1078 0.5967 0.6456 2.250 0.7255 0.01412 0.00618 -0.1079 0.5933 0.6504 2.500 0.7533 0.01424 0.00634 -0.1081 0.5898 0.6554 2.750 0.7809 0.01435 0.00650 -0.1082 0.5866 0.6597 3.000 0.8085 0.01447 0.00667 -0.1083 0.5839 0.6640 3.250 0.8371 0.01460 0.00682 -0.1086 0.5814 0.6690 3.500 0.8656 0.01475 0.00699 -0.1089 0.5784 0.6746 3.750 0.8911 0.01489 0.00724 -0.1087 0.5742 0.6794 4.000 0.9173 0.01502 0.00746 -0.1085 0.5702 0.6844 4.250 0.9447 0.01516 0.00766 -0.1086 0.5669 0.6904 4.500 0.9731 0.01530 0.00782 -0.1089 0.5640 0.6968 4.750 1.0002 0.01547 0.00806 -0.1088 0.5611 0.7022 5.000 1.0249 0.01566 0.00840 -0.1085 0.5572 0.7088 5.250 1.0508 0.01584 0.00866 -0.1084 0.5532 0.7156 5.500 1.0763 0.01595 0.00886 -0.1080 0.5486 0.7212 5.750 1.1019 0.01605 0.00900 -0.1077 0.5425 0.7280 6.000 1.1239 0.01617 0.00923 -0.1068 0.5344 0.7349 6.250 1.1485 0.01621 0.00929 -0.1062 0.5266 0.7412 6.500 1.1679 0.01635 0.00955 -0.1048 0.5165 0.7488 6.750 1.1905 0.01646 0.00971 -0.1039 0.5081 0.7559 7.000 1.2100 0.01663 0.01001 -0.1025 0.4990 0.7637 7.250 1.2303 0.01680 0.01024 -0.1013 0.4894 0.7721 7.500 1.2468 0.01697 0.01045 -0.0994 0.4767 0.7801 7.750 1.2604 0.01722 0.01077 -0.0971 0.4609 0.7894 8.000 1.2690 0.01748 0.01110 -0.0938 0.4435 0.7980 8.250 1.2767 0.01788 0.01154 -0.0905 0.4212 0.8082 8.500 1.2793 0.01846 0.01207 -0.0866 0.3912 0.8191 8.750 1.2743 0.01943 0.01290 -0.0818 0.3584 0.8312 9.000 1.2664 0.02076 0.01408 -0.0772 0.3271 0.8448 9.250 1.2581 0.02229 0.01551 -0.0729 0.2974 0.8602 9.500 1.2487 0.02399 0.01713 -0.0687 0.2684 0.8790 9.750 1.2392 0.02578 0.01887 -0.0648 0.2429 0.9058 10.000 1.2296 0.02757 0.02062 -0.0613 0.2197 1.0000 10.250 1.2269 0.02986 0.02279 -0.0596 0.1958 1.0000 10.500 1.2251 0.03218 0.02500 -0.0581 0.1739 1.0000 10.750 1.2237 0.03456 0.02729 -0.0568 0.1547 1.0000 11.000 1.2242 0.03687 0.02953 -0.0557 0.1371 1.0000 11.250 1.2251 0.03923 0.03184 -0.0548 0.1214 1.0000 11.500 1.2267 0.04160 0.03416 -0.0540 0.1077 1.0000 11.750 1.2292 0.04396 0.03648 -0.0534 0.0961 1.0000 12.000 1.2321 0.04635 0.03884 -0.0529 0.0858 1.0000 12.250 1.2355 0.04875 0.04122 -0.0524 0.0764 1.0000 12.500 1.2391 0.05119 0.04365 -0.0521 0.0688 1.0000 12.750 1.2436 0.05359 0.04605 -0.0518 0.0617 1.0000 13.000 1.2486 0.05599 0.04846 -0.0516 0.0561 1.0000 13.250 1.2528 0.05852 0.05101 -0.0515 0.0516 1.0000 13.500 1.2575 0.06103 0.05355 -0.0515 0.0475 1.0000 13.750 1.2623 0.06360 0.05616 -0.0515 0.0445 1.0000 14.000 1.2669 0.06623 0.05884 -0.0516 0.0416 1.0000 14.250 1.2711 0.06895 0.06161 -0.0518 0.0393 1.0000 14.500 1.2760 0.07161 0.06434 -0.0520 0.0372 1.0000 14.750 1.2790 0.07456 0.06732 -0.0523 0.0355 1.0000 15.000 1.2833 0.07740 0.07025 -0.0527 0.0340 1.0000 15.250 1.2874 0.08030 0.07324 -0.0531 0.0324 1.0000 15.500 1.2904 0.08338 0.07637 -0.0537 0.0311 1.0000 15.750 1.2924 0.08663 0.07968 -0.0543 0.0301 1.0000 16.000 1.2965 0.08962 0.08277 -0.0549 0.0288 1.0000 16.250 1.2995 0.09281 0.08604 -0.0556 0.0277 1.0000 16.500 1.3016 0.09614 0.08944 -0.0565 0.0269 1.0000