XFOIL Version 6.96 Calculated polar for: NACA 66(3)-418 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.8717 0.08368 0.08065 -0.1009 0.9576 0.0130 -19.500 -0.8852 0.07549 0.07225 -0.1082 0.9530 0.0129 -19.250 -0.8854 0.06916 0.06575 -0.1150 0.9474 0.0130 -19.000 -0.8780 0.06431 0.06075 -0.1208 0.9389 0.0131 -18.750 -0.8744 0.05978 0.05605 -0.1254 0.9276 0.0132 -18.500 -0.8734 0.05611 0.05220 -0.1281 0.9140 0.0133 -18.250 -0.8764 0.05274 0.04867 -0.1294 0.9011 0.0134 -18.000 -0.8763 0.05004 0.04582 -0.1302 0.8907 0.0135 -17.750 -0.8787 0.04730 0.04292 -0.1306 0.8812 0.0135 -17.500 -0.8773 0.04498 0.04049 -0.1308 0.8734 0.0137 -17.000 -0.8735 0.04084 0.03610 -0.1304 0.8586 0.0138 -16.750 -0.8691 0.03910 0.03425 -0.1301 0.8524 0.0138 -16.250 -0.8592 0.03583 0.03076 -0.1290 0.8418 0.0141 -16.000 -0.8515 0.03447 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-0.0759 0.7116 0.6930 -1.250 0.1927 0.00647 0.00198 -0.0764 0.7109 0.6991 -1.000 0.2221 0.00651 0.00200 -0.0770 0.7102 0.7030 -0.750 0.2515 0.00654 0.00202 -0.0775 0.7094 0.7057 -0.500 0.2806 0.00653 0.00202 -0.0780 0.7084 0.7076 -0.250 0.3099 0.00653 0.00203 -0.0786 0.7076 0.7085 0.000 0.3392 0.00654 0.00204 -0.0792 0.7067 0.7093 0.250 0.3685 0.00655 0.00206 -0.0797 0.7059 0.7101 0.500 0.3977 0.00657 0.00208 -0.0803 0.7050 0.7110 0.750 0.4269 0.00658 0.00211 -0.0808 0.7039 0.7118 1.000 0.4557 0.00659 0.00212 -0.0813 0.7021 0.7127 1.250 0.4844 0.00660 0.00212 -0.0817 0.6994 0.7135 1.500 0.5131 0.00662 0.00212 -0.0821 0.6964 0.7144 1.750 0.5418 0.00665 0.00216 -0.0826 0.6942 0.7153 2.000 0.5700 0.00665 0.00219 -0.0829 0.6919 0.7162 2.250 0.5981 0.00666 0.00222 -0.0832 0.6887 0.7173 2.500 0.6259 0.00667 0.00224 -0.0834 0.6850 0.7183 2.750 0.6537 0.00669 0.00226 -0.0837 0.6812 0.7194 3.000 0.6810 0.00672 0.00230 -0.0838 0.6766 0.7203 3.250 0.7077 0.00672 0.00233 -0.0838 0.6695 0.7211 3.500 0.7336 0.00677 0.00235 -0.0836 0.6630 0.7219 3.750 0.7601 0.00679 0.00241 -0.0836 0.6548 0.7227 4.000 0.7836 0.00684 0.00245 -0.0830 0.6405 0.7240 4.250 0.7945 0.00708 0.00253 -0.0797 0.5923 0.7254 4.500 0.7791 0.00777 0.00291 -0.0711 0.5273 0.7271 4.750 0.7605 0.00868 0.00354 -0.0622 0.4666 0.7290 5.000 0.7479 0.00967 0.00428 -0.0551 0.4091 0.7309 5.250 0.7394 0.01072 0.00507 -0.0490 0.3548 0.7327 5.500 0.7377 0.01167 0.00581 -0.0444 0.3079 0.7344 5.750 0.7415 0.01252 0.00649 -0.0409 0.2708 0.7360 6.000 0.7410 0.01360 0.00732 -0.0369 0.2210 0.7376 6.250 0.7452 0.01455 0.00808 -0.0337 0.1790 0.7390 6.500 0.7489 0.01559 0.00889 -0.0305 0.1342 0.7404 6.750 0.7585 0.01638 0.00957 -0.0282 0.1046 0.7422 7.000 0.7683 0.01721 0.01027 -0.0261 0.0780 0.7440 7.250 0.7820 0.01787 0.01086 -0.0245 0.0607 0.7459 7.500 0.7958 0.01855 0.01147 -0.0230 0.0454 0.7477 7.750 0.8109 0.01918 0.01207 -0.0217 0.0367 0.7497 8.000 0.8279 0.01973 0.01260 -0.0207 0.0322 0.7517 8.250 0.8454 0.02027 0.01314 -0.0197 0.0288 0.7535 8.500 0.8621 0.02086 0.01372 -0.0187 0.0258 0.7552 8.750 0.8797 0.02141 0.01428 -0.0179 0.0241 0.7568 9.000 0.8966 0.02201 0.01487 -0.0170 0.0222 0.7585 9.250 0.9143 0.02256 0.01545 -0.0161 0.0206 0.7607 9.500 0.9309 0.02317 0.01608 -0.0152 0.0188 0.7629 9.750 0.9476 0.02380 0.01673 -0.0143 0.0177 0.7651 10.000 0.9645 0.02443 0.01737 -0.0135 0.0163 0.7673 10.250 0.9812 0.02508 0.01804 -0.0127 0.0156 0.7697 10.500 0.9974 0.02577 0.01875 -0.0118 0.0146 0.7719 10.750 1.0137 0.02648 0.01948 -0.0110 0.0140 0.7741 11.250 1.0447 0.02799 0.02104 -0.0093 0.0124 0.7788 11.500 1.0603 0.02875 0.02184 -0.0085 0.0121 0.7815 11.750 1.0751 0.02958 0.02271 -0.0077 0.0118 0.7844 12.000 1.0905 0.03039 0.02356 -0.0069 0.0114 0.7872 12.250 1.1053 0.03125 0.02446 -0.0061 0.0113 0.7900 12.500 1.1197 0.03216 0.02540 -0.0054 0.0108 0.7926 12.750 1.1334 0.03313 0.02640 -0.0046 0.0106 0.7954 13.000 1.1466 0.03413 0.02745 -0.0037 0.0103 0.7986 13.250 1.1598 0.03514 0.02851 -0.0029 0.0101 0.8019 13.500 1.1721 0.03626 0.02968 -0.0021 0.0100 0.8053 13.750 1.1835 0.03747 0.03093 -0.0013 0.0098 0.8087 14.250 1.2067 0.03990 0.03349 0.0002 0.0097 0.8158 14.500 1.2187 0.04110 0.03476 0.0008 0.0095 0.8197 14.750 1.2295 0.04242 0.03615 0.0015 0.0094 0.8240 15.000 1.2406 0.04376 0.03755 0.0021 0.0093 0.8277 15.250 1.2495 0.04529 0.03915 0.0028 0.0093 0.8316 15.500 1.2592 0.04677 0.04071 0.0034 0.0092 0.8360 15.750 1.2678 0.04840 0.04242 0.0040 0.0090 0.8405 16.000 1.2767 0.05004 0.04413 0.0044 0.0090 0.8448 16.250 1.2841 0.05182 0.04599 0.0049 0.0088 0.8493 16.500 1.2906 0.05372 0.04797 0.0054 0.0088 0.8545 16.750 1.2975 0.05563 0.04997 0.0057 0.0088 0.8598 17.000 1.3039 0.05763 0.05205 0.0060 0.0087 0.8652 17.250 1.3092 0.05976 0.05428 0.0063 0.0086 0.8718 17.500 1.3137 0.06203 0.05665 0.0065 0.0086 0.8786 17.750 1.3165 0.06450 0.05923 0.0067 0.0085 0.8863 18.000 1.3206 0.06688 0.06169 0.0067 0.0084 0.8953 18.250 1.3240 0.06931 0.06423 0.0067 0.0083 0.9063 18.500 1.3242 0.07221 0.06724 0.0066 0.0082 0.9177 18.750 1.3251 0.07506 0.07021 0.0064 0.0082 0.9323 19.000 1.3270 0.07823 0.07352 0.0054 0.0081 0.9551 19.250 1.3277 0.08201 0.07741 0.0037 0.0080 1.0000