XFOIL Version 6.96 Calculated polar for: NACA 642-015 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -1.0588 0.12198 0.11875 0.0051 1.0000 0.0128 -18.750 -1.0769 0.11368 0.11029 0.0000 1.0000 0.0128 -18.500 -1.0954 0.10563 0.10207 -0.0047 1.0000 0.0128 -18.250 -1.1090 0.09879 0.09508 -0.0086 1.0000 0.0129 -18.000 -1.1203 0.09265 0.08879 -0.0120 1.0000 0.0129 -17.750 -1.1288 0.08719 0.08321 -0.0149 1.0000 0.0130 -17.500 -1.1369 0.08200 0.07788 -0.0175 1.0000 0.0131 -17.250 -1.1427 0.07738 0.07313 -0.0197 1.0000 0.0132 -17.000 -1.1476 0.07306 0.06869 -0.0216 1.0000 0.0132 -16.750 -1.1509 0.06907 0.06458 -0.0233 1.0000 0.0134 -16.500 -1.1522 0.06551 0.06090 -0.0247 1.0000 0.0136 -16.250 -1.1545 0.06195 0.05721 -0.0258 1.0000 0.0137 -16.000 -1.1543 0.05880 0.05395 -0.0268 1.0000 0.0139 -15.750 -1.1545 0.05571 0.05074 -0.0275 1.0000 0.0139 -15.500 -1.1522 0.05300 0.04792 -0.0281 1.0000 0.0142 -15.250 -1.1494 0.05046 0.04527 -0.0285 1.0000 0.0143 -15.000 -1.1460 0.04803 0.04273 -0.0288 1.0000 0.0144 -14.750 -1.1417 0.04578 0.04037 -0.0289 1.0000 0.0145 -14.500 -1.1370 0.04365 0.03812 -0.0289 1.0000 0.0147 -14.250 -1.1309 0.04169 0.03608 -0.0288 1.0000 0.0148 -14.000 -1.1285 0.03943 0.03375 -0.0285 1.0000 0.0150 -13.750 -1.1228 0.03754 0.03180 -0.0282 1.0000 0.0151 -13.500 -1.1161 0.03579 0.02998 -0.0278 1.0000 0.0153 -13.250 -1.1087 0.03413 0.02827 -0.0274 1.0000 0.0155 -13.000 -1.0996 0.03265 0.02672 -0.0269 1.0000 0.0157 -12.750 -1.0897 0.03127 0.02529 -0.0264 1.0000 0.0160 -12.500 -1.0797 0.02994 0.02390 -0.0258 1.0000 0.0163 -12.250 -1.0689 0.02868 0.02259 -0.0251 1.0000 0.0165 -12.000 -1.0581 0.02747 0.02132 -0.0244 1.0000 0.0169 -11.750 -1.0464 0.02634 0.02014 -0.0236 1.0000 0.0173 -11.500 -1.0340 0.02530 0.01903 -0.0228 1.0000 0.0177 -11.250 -1.0217 0.02428 0.01794 -0.0219 1.0000 0.0180 -11.000 -1.0089 0.02332 0.01692 -0.0209 1.0000 0.0183 -10.750 -0.9995 0.02217 0.01575 -0.0197 1.0000 0.0188 -10.500 -0.9875 0.02124 0.01479 -0.0185 1.0000 0.0191 -10.250 -0.9680 0.02042 0.01393 -0.0186 0.9606 0.0198 -10.000 -0.9447 0.01967 0.01309 -0.0192 0.9249 0.0204 -9.750 -0.9335 0.01909 0.01239 -0.0171 0.8993 0.0209 -9.500 -0.9226 0.01854 0.01174 -0.0148 0.8804 0.0214 -9.250 -0.9107 0.01807 0.01115 -0.0125 0.8649 0.0221 -9.000 -0.8977 0.01760 0.01059 -0.0104 0.8519 0.0227 -8.750 -0.8822 0.01706 0.00999 -0.0088 0.8399 0.0237 -8.500 -0.8639 0.01660 0.00948 -0.0075 0.8293 0.0247 -8.250 -0.8445 0.01620 0.00900 -0.0064 0.8196 0.0259 -8.000 -0.8236 0.01582 0.00854 -0.0056 0.8097 0.0271 -7.750 -0.8030 0.01539 0.00806 -0.0046 0.8010 0.0285 -7.500 -0.7817 0.01499 0.00762 -0.0038 0.7919 0.0304 -7.250 -0.7591 0.01464 0.00722 -0.0032 0.7839 0.0324 -7.000 -0.7361 0.01429 0.00682 -0.0026 0.7757 0.0344 -6.750 -0.7131 0.01393 0.00643 -0.0021 0.7684 0.0372 -6.500 -0.6891 0.01362 0.00608 -0.0016 0.7602 0.0405 -6.250 -0.6655 0.01326 0.00572 -0.0011 0.7527 0.0462 -6.000 -0.6414 0.01291 0.00537 -0.0008 0.7448 0.0540 -5.750 -0.6175 0.01255 0.00503 -0.0003 0.7377 0.0668 -5.500 -0.5934 0.01215 0.00470 0.0000 0.7306 0.0847 -5.250 -0.5696 0.01171 0.00435 0.0004 0.7236 0.1107 -5.000 -0.5462 0.01120 0.00399 0.0008 0.7171 0.1494 -4.750 -0.5229 0.01065 0.00363 0.0012 0.7102 0.1975 -4.500 -0.5007 0.00997 0.00321 0.0017 0.7039 0.2647 -4.250 -0.4789 0.00917 0.00279 0.0022 0.6973 0.3520 -4.000 -0.4553 0.00865 0.00255 0.0026 0.6906 0.4295 -3.750 -0.4281 0.00849 0.00243 0.0026 0.6842 0.4599 -3.500 -0.4008 0.00834 0.00234 0.0026 0.6775 0.4855 -3.250 -0.3731 0.00826 0.00227 0.0026 0.6716 0.5086 -3.000 -0.3451 0.00818 0.00221 0.0025 0.6656 0.5273 -2.750 -0.3171 0.00812 0.00218 0.0024 0.6597 0.5453 -2.500 -0.2887 0.00811 0.00213 0.0023 0.6544 0.5577 -2.250 -0.2601 0.00805 0.00208 0.0021 0.6488 0.5633 -2.000 -0.2313 0.00803 0.00202 0.0019 0.6433 0.5686 -1.750 -0.2024 0.00803 0.00196 0.0017 0.6383 0.5742 -1.500 -0.1736 0.00798 0.00192 0.0014 0.6331 0.5788 -1.250 -0.1447 0.00796 0.00189 0.0012 0.6278 0.5831 -1.000 -0.1159 0.00797 0.00185 0.0010 0.6228 0.5875 -0.750 -0.0867 0.00795 0.00182 0.0007 0.6177 0.5915 -0.500 -0.0579 0.00793 0.00180 0.0005 0.6127 0.5954 -0.250 -0.0291 0.00793 0.00179 0.0003 0.6083 0.5997 0.000 0.0000 0.00794 0.00179 0.0000 0.6042 0.6041 0.250 0.0291 0.00793 0.00179 -0.0003 0.5997 0.6083 0.500 0.0579 0.00793 0.00180 -0.0005 0.5954 0.6127 0.750 0.0867 0.00795 0.00182 -0.0007 0.5915 0.6176 1.000 0.1159 0.00797 0.00185 -0.0010 0.5875 0.6228 1.250 0.1447 0.00796 0.00189 -0.0012 0.5831 0.6278 1.500 0.1736 0.00798 0.00192 -0.0014 0.5788 0.6331 1.750 0.2024 0.00803 0.00196 -0.0017 0.5742 0.6383 2.000 0.2313 0.00803 0.00202 -0.0019 0.5685 0.6433 2.250 0.2600 0.00805 0.00208 -0.0021 0.5633 0.6488 2.500 0.2887 0.00811 0.00213 -0.0023 0.5577 0.6544 2.750 0.3171 0.00812 0.00218 -0.0024 0.5454 0.6597 3.000 0.3450 0.00818 0.00221 -0.0025 0.5272 0.6656 3.250 0.3731 0.00826 0.00227 -0.0026 0.5090 0.6716 3.500 0.4008 0.00834 0.00234 -0.0026 0.4854 0.6775 3.750 0.4281 0.00849 0.00243 -0.0026 0.4599 0.6842 4.000 0.4553 0.00865 0.00255 -0.0026 0.4295 0.6906 4.250 0.4789 0.00918 0.00279 -0.0022 0.3519 0.6972 4.500 0.5008 0.00995 0.00320 -0.0017 0.2662 0.7039 4.750 0.5230 0.01064 0.00363 -0.0012 0.1979 0.7101 5.000 0.5462 0.01120 0.00399 -0.0008 0.1493 0.7171 5.250 0.5697 0.01171 0.00435 -0.0004 0.1108 0.7236 5.500 0.5934 0.01215 0.00470 0.0000 0.0845 0.7306 5.750 0.6175 0.01255 0.00503 0.0003 0.0665 0.7377 6.000 0.6415 0.01291 0.00537 0.0007 0.0541 0.7448 6.250 0.6656 0.01326 0.00572 0.0011 0.0462 0.7528 6.500 0.6892 0.01362 0.00608 0.0016 0.0406 0.7602 6.750 0.7132 0.01393 0.00643 0.0020 0.0372 0.7683 7.000 0.7362 0.01430 0.00682 0.0026 0.0344 0.7757 7.250 0.7592 0.01464 0.00722 0.0032 0.0324 0.7838 7.500 0.7819 0.01499 0.00762 0.0038 0.0304 0.7920 7.750 0.8033 0.01539 0.00806 0.0046 0.0286 0.8010 8.000 0.8239 0.01582 0.00854 0.0055 0.0270 0.8097 8.250 0.8447 0.01620 0.00900 0.0064 0.0259 0.8195 8.500 0.8642 0.01661 0.00948 0.0075 0.0247 0.8293 8.750 0.8825 0.01706 0.00999 0.0087 0.0237 0.8399 9.000 0.8979 0.01761 0.01059 0.0104 0.0227 0.8518 9.250 0.9112 0.01807 0.01116 0.0125 0.0221 0.8648 9.500 0.9228 0.01856 0.01175 0.0148 0.0215 0.8802 9.750 0.9339 0.01909 0.01239 0.0170 0.0209 0.8991 10.000 0.9450 0.01968 0.01310 0.0191 0.0203 0.9248 10.250 0.9689 0.02040 0.01392 0.0185 0.0196 0.9603 10.500 0.9883 0.02123 0.01478 0.0184 0.0191 1.0000 10.750 1.0001 0.02218 0.01575 0.0195 0.0187 1.0000 11.000 1.0103 0.02328 0.01688 0.0208 0.0182 1.0000 11.250 1.0229 0.02425 0.01792 0.0217 0.0179 1.0000 11.500 1.0351 0.02528 0.01900 0.0226 0.0176 1.0000 11.750 1.0467 0.02638 0.02018 0.0235 0.0173 1.0000 12.000 1.0590 0.02746 0.02131 0.0242 0.0170 1.0000 12.250 1.0700 0.02867 0.02257 0.0250 0.0165 1.0000 12.500 1.0805 0.02994 0.02390 0.0256 0.0163 1.0000 12.750 1.0908 0.03125 0.02527 0.0262 0.0160 1.0000 13.000 1.1006 0.03265 0.02672 0.0268 0.0158 1.0000 13.250 1.1090 0.03418 0.02832 0.0273 0.0156 1.0000 13.500 1.1176 0.03574 0.02994 0.0277 0.0154 1.0000 13.750 1.1241 0.03751 0.03177 0.0281 0.0152 1.0000 14.000 1.1289 0.03949 0.03381 0.0284 0.0150 1.0000 14.250 1.1324 0.04165 0.03603 0.0286 0.0148 1.0000 14.500 1.1383 0.04363 0.03811 0.0287 0.0147 1.0000 14.750 1.1430 0.04577 0.04035 0.0287 0.0145 1.0000 15.000 1.1474 0.04800 0.04269 0.0286 0.0145 1.0000 15.250 1.1511 0.05041 0.04522 0.0283 0.0143 1.0000 15.500 1.1533 0.05302 0.04794 0.0279 0.0142 1.0000 15.750 1.1550 0.05581 0.05085 0.0273 0.0140 1.0000 16.000 1.1556 0.05881 0.05397 0.0266 0.0139 1.0000 16.250 1.1574 0.06178 0.05704 0.0256 0.0137 1.0000 16.500 1.1545 0.06540 0.06079 0.0245 0.0136 1.0000 16.750 1.1529 0.06902 0.06453 0.0230 0.0134 1.0000 17.000 1.1492 0.07305 0.06867 0.0214 0.0133 1.0000 17.250 1.1441 0.07740 0.07316 0.0195 0.0132 1.0000 17.500 1.1392 0.08193 0.07780 0.0173 0.0131 1.0000 17.750 1.1305 0.08720 0.08321 0.0146 0.0130 1.0000 18.000 1.1224 0.09262 0.08876 0.0117 0.0129 1.0000 18.250 1.1107 0.09882 0.09511 0.0083 0.0129 1.0000 18.500 1.0959 0.10589 0.10234 0.0043 0.0129 1.0000