XFOIL Version 6.96 Calculated polar for: NACA 65(3)-618 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 -0.9488 0.08351 0.08047 -0.0867 1.0000 0.0130 -19.500 -0.9664 0.07720 0.07403 -0.0902 1.0000 0.0131 -19.250 -0.9779 0.07205 0.06876 -0.0929 1.0000 0.0132 -19.000 -0.9873 0.06734 0.06395 -0.0953 1.0000 0.0134 -18.750 -0.9950 0.06308 0.05958 -0.0974 1.0000 0.0134 -18.500 -1.0004 0.05930 0.05569 -0.0991 1.0000 0.0136 -18.250 -1.0023 0.05609 0.05239 -0.1003 1.0000 0.0137 -18.000 -1.0035 0.05309 0.04930 -0.1014 1.0000 0.0138 -17.750 -1.0047 0.05023 0.04636 -0.1022 1.0000 0.0139 -17.500 -1.0051 0.04757 0.04363 -0.1028 1.0000 0.0141 -17.250 -1.0046 0.04512 0.04112 -0.1033 1.0000 0.0142 -17.000 -1.0001 0.04307 0.03901 -0.1036 0.9999 0.0144 -16.750 -0.9901 0.04092 0.03681 -0.1046 0.9874 0.0146 -16.500 -0.9696 0.03896 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-0.1118 0.6266 0.5589 -1.750 0.3020 0.00681 0.00170 -0.1123 0.6242 0.5765 -1.500 0.3313 0.00681 0.00173 -0.1127 0.6217 0.5874 -1.250 0.3605 0.00684 0.00173 -0.1131 0.6193 0.5918 -1.000 0.3895 0.00688 0.00173 -0.1135 0.6168 0.5939 -0.750 0.4183 0.00692 0.00174 -0.1139 0.6142 0.5963 -0.500 0.4478 0.00692 0.00176 -0.1144 0.6121 0.5989 -0.250 0.4771 0.00693 0.00177 -0.1148 0.6099 0.6012 0.000 0.5063 0.00695 0.00180 -0.1153 0.6076 0.6037 0.250 0.5353 0.00698 0.00182 -0.1157 0.6053 0.6063 0.500 0.5642 0.00702 0.00185 -0.1161 0.6029 0.6088 0.750 0.5929 0.00707 0.00189 -0.1164 0.6004 0.6110 1.250 0.6505 0.00715 0.00197 -0.1171 0.5961 0.6153 1.500 0.6796 0.00717 0.00202 -0.1176 0.5941 0.6179 1.750 0.7085 0.00721 0.00208 -0.1180 0.5918 0.6208 2.000 0.7372 0.00725 0.00214 -0.1183 0.5893 0.6236 2.250 0.7657 0.00730 0.00220 -0.1187 0.5869 0.6261 2.500 0.7940 0.00736 0.00226 -0.1189 0.5845 0.6285 2.750 0.8217 0.00745 0.00233 -0.1191 0.5816 0.6306 3.000 0.8503 0.00747 0.00240 -0.1195 0.5782 0.6334 3.250 0.8784 0.00751 0.00248 -0.1197 0.5736 0.6362 3.500 0.9058 0.00758 0.00256 -0.1198 0.5689 0.6394 3.750 0.9326 0.00768 0.00266 -0.1198 0.5644 0.6426 4.000 0.9604 0.00773 0.00274 -0.1201 0.5583 0.6457 4.250 0.9853 0.00786 0.00284 -0.1197 0.5476 0.6483 4.500 1.0115 0.00794 0.00294 -0.1196 0.5372 0.6512 4.750 1.0363 0.00807 0.00306 -0.1192 0.5253 0.6545 5.000 1.0575 0.00831 0.00323 -0.1181 0.5027 0.6578 5.250 1.0731 0.00873 0.00349 -0.1161 0.4661 0.6612 5.500 1.0824 0.00937 0.00390 -0.1128 0.4182 0.6647 5.750 1.0806 0.01017 0.00443 -0.1075 0.3642 0.6682 6.000 1.0784 0.01109 0.00511 -0.1023 0.3132 0.6723 6.250 1.0778 0.01202 0.00583 -0.0977 0.2680 0.6765 6.500 1.0784 0.01296 0.00659 -0.0934 0.2281 0.6806 6.750 1.0813 0.01390 0.00736 -0.0898 0.1951 0.6843 7.000 1.0838 0.01491 0.00824 -0.0863 0.1629 0.6882 7.250 1.0873 0.01596 0.00917 -0.0831 0.1345 0.6927 7.500 1.0914 0.01705 0.01015 -0.0801 0.1084 0.6973 7.750 1.0969 0.01815 0.01116 -0.0775 0.0860 0.7017 8.000 1.1047 0.01920 0.01214 -0.0754 0.0700 0.7062 8.250 1.1120 0.02030 0.01320 -0.0732 0.0546 0.7114 8.500 1.1194 0.02147 0.01431 -0.0712 0.0406 0.7168 8.750 1.1307 0.02245 0.01527 -0.0697 0.0338 0.7216 9.000 1.1420 0.02344 0.01627 -0.0683 0.0290 0.7265 9.250 1.1551 0.02435 0.01721 -0.0671 0.0265 0.7319 9.500 1.1680 0.02530 0.01819 -0.0659 0.0245 0.7374 9.750 1.1813 0.02625 0.01917 -0.0648 0.0229 0.7424 10.000 1.1933 0.02730 0.02025 -0.0637 0.0214 0.7483 10.250 1.2072 0.02825 0.02125 -0.0628 0.0204 0.7548 10.500 1.2198 0.02931 0.02235 -0.0618 0.0193 0.7608 10.750 1.2321 0.03041 0.02349 -0.0608 0.0183 0.7678 11.000 1.2445 0.03154 0.02467 -0.0599 0.0175 0.7748 11.250 1.2574 0.03263 0.02581 -0.0591 0.0167 0.7814 11.500 1.2691 0.03385 0.02708 -0.0582 0.0158 0.7888 11.750 1.2806 0.03511 0.02838 -0.0574 0.0152 0.7958 12.000 1.2921 0.03640 0.02972 -0.0566 0.0146 0.8038 12.250 1.3040 0.03767 0.03105 -0.0559 0.0141 0.8120 12.500 1.3157 0.03896 0.03242 -0.0552 0.0136 0.8211 12.750 1.3263 0.04038 0.03389 -0.0545 0.0131 0.8306 13.000 1.3369 0.04180 0.03537 -0.0538 0.0127 0.8408 13.250 1.3461 0.04338 0.03702 -0.0531 0.0123 0.8511 13.500 1.3566 0.04485 0.03856 -0.0524 0.0119 0.8627 13.750 1.3664 0.04635 0.04015 -0.0518 0.0116 0.8768 14.000 1.3749 0.04792 0.04182 -0.0510 0.0114 0.8954 14.250 1.3828 0.04938 0.04339 -0.0499 0.0111 0.9257 14.750 1.4009 0.05285 0.04701 -0.0493 0.0106 1.0000 15.250 1.4173 0.05677 0.05101 -0.0488 0.0102 1.0000 15.500 1.4240 0.05894 0.05322 -0.0486 0.0099 1.0000 15.750 1.4311 0.06111 0.05545 -0.0485 0.0098 1.0000 16.000 1.4391 0.06320 0.05759 -0.0484 0.0097 1.0000 16.250 1.4458 0.06548 0.05994 -0.0484 0.0095 1.0000 16.500 1.4528 0.06775 0.06226 -0.0485 0.0094 1.0000 16.750 1.4588 0.07015 0.06473 -0.0486 0.0093 1.0000 17.000 1.4642 0.07267 0.06731 -0.0488 0.0092 1.0000 17.250 1.4694 0.07525 0.06996 -0.0490 0.0091 1.0000 17.500 1.4742 0.07793 0.07271 -0.0493 0.0090 1.0000 17.750 1.4784 0.08072 0.07556 -0.0497 0.0089 1.0000 18.000 1.4822 0.08358 0.07849 -0.0502 0.0088 1.0000 18.250 1.4849 0.08662 0.08161 -0.0508 0.0087 1.0000 18.500 1.4876 0.08972 0.08477 -0.0514 0.0086 1.0000 18.750 1.4893 0.09299 0.08811 -0.0522 0.0085 1.0000 19.000 1.4912 0.09626 0.09146 -0.0530 0.0085 1.0000 19.250 1.4915 0.09983 0.09510 -0.0540 0.0083 1.0000