XFOIL Version 6.96 Calculated polar for: NACA 67 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 ------ -------- --------- --------- -------- -------- -------- -17.750 -0.6768 0.10901 0.10621 -0.0794 0.9717 0.0135 -17.500 -0.7888 0.08096 0.07773 -0.0954 0.9709 0.0132 -17.250 -0.8197 0.06977 0.06628 -0.1039 0.9681 0.0131 -17.000 -0.8367 0.06173 0.05798 -0.1105 0.9649 0.0131 -16.750 -0.8447 0.05582 0.05184 -0.1154 0.9612 0.0133 -16.500 -0.8498 0.05108 0.04689 -0.1188 0.9568 0.0133 -16.250 -0.8529 0.04708 0.04266 -0.1212 0.9523 0.0134 -16.000 -0.8556 0.04382 0.03921 -0.1222 0.9475 0.0135 -15.750 -0.8563 0.04128 0.03647 -0.1223 0.9423 0.0136 -15.500 -0.8561 0.03896 0.03395 -0.1220 0.9376 0.0137 -15.250 -0.8561 0.03694 0.03177 -0.1210 0.9332 0.0138 -15.000 -0.8554 0.03513 0.02980 -0.1196 0.9286 0.0139 -14.750 -0.8540 0.03340 0.02795 -0.1182 0.9244 0.0141 -14.500 -0.8487 0.03205 0.02650 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-5.000 -0.2088 0.01231 0.00498 -0.0725 0.8498 0.0631 -4.750 -0.1890 0.01208 0.00480 -0.0712 0.8487 0.0743 -4.500 -0.1704 0.01180 0.00461 -0.0698 0.8476 0.0944 -4.250 -0.1531 0.01151 0.00443 -0.0681 0.8465 0.1247 -4.000 -0.1379 0.01118 0.00427 -0.0660 0.8454 0.1663 -3.750 -0.1259 0.01083 0.00413 -0.0633 0.8442 0.2195 -3.500 -0.1157 0.01049 0.00400 -0.0601 0.8428 0.2780 -3.250 -0.1095 0.01015 0.00393 -0.0561 0.8411 0.3440 -3.000 -0.1041 0.00976 0.00384 -0.0520 0.8393 0.4177 -2.750 -0.1021 0.00928 0.00371 -0.0471 0.8372 0.5051 -2.500 -0.1038 0.00861 0.00354 -0.0413 0.8349 0.6192 -2.250 -0.0918 0.00840 0.00383 -0.0378 0.8333 0.7344 -2.000 -0.0676 0.00855 0.00401 -0.0370 0.8324 0.7681 -1.750 -0.0426 0.00876 0.00424 -0.0363 0.8314 0.7895 -1.500 -0.0164 0.00916 0.00466 -0.0356 0.8305 0.8093 -1.250 0.0136 0.00952 0.00505 -0.0357 0.8297 0.8188 -1.000 0.0422 0.00966 0.00517 -0.0359 0.8289 0.8230 -0.750 0.0699 0.00964 0.00512 -0.0361 0.8280 0.8251 -0.500 0.0960 0.00962 0.00507 -0.0360 0.8269 0.8272 -0.250 0.1159 0.00965 0.00509 -0.0347 0.8248 0.8294 0.000 0.1400 0.00970 0.00516 -0.0342 0.8228 0.8305 0.250 0.1652 0.00975 0.00523 -0.0339 0.8209 0.8316 0.500 0.1913 0.00977 0.00526 -0.0337 0.8192 0.8326 0.750 0.2182 0.00977 0.00527 -0.0337 0.8176 0.8335 1.000 0.2462 0.00976 0.00526 -0.0340 0.8161 0.8346 1.250 0.2761 0.00969 0.00520 -0.0346 0.8146 0.8355 1.500 0.3093 0.00955 0.00505 -0.0358 0.8126 0.8362 1.750 0.3303 0.00949 0.00502 -0.0345 0.8074 0.8375 2.000 0.3557 0.00931 0.00485 -0.0340 0.8013 0.8388 2.250 0.3922 0.00900 0.00450 -0.0357 0.7957 0.8395 2.500 0.4066 0.00889 0.00443 -0.0330 0.7855 0.8411 2.750 0.4275 0.00870 0.00425 -0.0315 0.7740 0.8424 3.000 0.4429 0.00853 0.00408 -0.0289 0.7555 0.8438 3.250 0.4607 0.00833 0.00380 -0.0267 0.7233 0.8452 3.500 0.4658 0.00840 0.00348 -0.0216 0.6450 0.8468 3.750 0.4504 0.00896 0.00371 -0.0127 0.5730 0.8488 4.000 0.4413 0.00967 0.00414 -0.0055 0.5107 0.8509 4.250 0.4387 0.01036 0.00457 0.0000 0.4514 0.8528 4.500 0.4412 0.01102 0.00498 0.0045 0.3918 0.8546 4.750 0.4474 0.01166 0.00536 0.0080 0.3332 0.8565 5.000 0.4563 0.01230 0.00573 0.0110 0.2738 0.8584 5.250 0.4680 0.01288 0.00606 0.0135 0.2199 0.8599 5.500 0.4827 0.01339 0.00637 0.0153 0.1774 0.8612 5.750 0.4986 0.01386 0.00669 0.0170 0.1405 0.8623 6.000 0.5155 0.01430 0.00701 0.0185 0.1116 0.8635 6.250 0.5328 0.01474 0.00734 0.0199 0.0872 0.8646 6.500 0.5510 0.01514 0.00767 0.0212 0.0696 0.8658 6.750 0.5697 0.01554 0.00801 0.0224 0.0579 0.8670 7.000 0.5892 0.01590 0.00835 0.0234 0.0515 0.8683 7.250 0.6084 0.01628 0.00870 0.0244 0.0451 0.8696 7.500 0.6285 0.01661 0.00905 0.0253 0.0418 0.8711 7.750 0.6480 0.01698 0.00941 0.0263 0.0386 0.8728 8.000 0.6673 0.01737 0.00980 0.0273 0.0361 0.8744 8.250 0.6875 0.01771 0.01017 0.0281 0.0342 0.8759 8.500 0.7071 0.01810 0.01057 0.0290 0.0323 0.8773 8.750 0.7258 0.01853 0.01100 0.0300 0.0303 0.8787 9.000 0.7444 0.01894 0.01146 0.0310 0.0293 0.8801 9.250 0.7633 0.01933 0.01191 0.0320 0.0276 0.8816 9.500 0.7817 0.01977 0.01237 0.0330 0.0262 0.8832 9.750 0.7991 0.02029 0.01290 0.0342 0.0247 0.8850 10.000 0.8173 0.02075 0.01342 0.0351 0.0236 0.8868 10.250 0.8355 0.02122 0.01394 0.0361 0.0218 0.8888 10.500 0.8527 0.02175 0.01449 0.0372 0.0207 0.8908 10.750 0.8694 0.02234 0.01511 0.0383 0.0195 0.8929 11.000 0.8864 0.02290 0.01572 0.0393 0.0184 0.8948 11.250 0.9026 0.02347 0.01635 0.0405 0.0176 0.8969 11.500 0.9174 0.02413 0.01705 0.0418 0.0166 0.8993 11.750 0.9321 0.02482 0.01779 0.0431 0.0161 0.9019 12.000 0.9466 0.02554 0.01858 0.0443 0.0154 0.9047 12.250 0.9613 0.02625 0.01936 0.0455 0.0152 0.9073 12.500 0.9752 0.02704 0.02022 0.0467 0.0146 0.9100 12.750 0.9883 0.02783 0.02108 0.0480 0.0143 0.9125 13.000 1.0008 0.02867 0.02199 0.0494 0.0141 0.9154 13.250 1.0124 0.02959 0.02297 0.0507 0.0136 0.9186 13.500 1.0228 0.03062 0.02406 0.0521 0.0133 0.9220 13.750 1.0319 0.03180 0.02531 0.0535 0.0131 0.9253 14.000 1.0414 0.03290 0.02653 0.0549 0.0130 0.9286 14.250 1.0501 0.03409 0.02782 0.0563 0.0130 0.9326 14.500 1.0579 0.03541 0.02926 0.0576 0.0127 0.9367 14.750 1.0662 0.03673 0.03069 0.0588 0.0126 0.9408 15.000 1.0742 0.03818 0.03226 0.0597 0.0124 0.9454 15.250 1.0823 0.03974 0.03393 0.0604 0.0123 0.9505 15.500 1.0913 0.04153 0.03586 0.0605 0.0121 0.9552 15.750 1.0999 0.04361 0.03807 0.0602 0.0120 0.9602 16.000 1.1095 0.04578 0.04038 0.0595 0.0119 0.9656 16.250 1.1193 0.04814 0.04288 0.0583 0.0118 0.9715 16.500 1.1240 0.05088 0.04577 0.0573 0.0117 0.9893 16.750 1.1237 0.05336 0.04835 0.0578 0.0115 1.0000 17.000 1.1243 0.05606 0.05115 0.0577 0.0113 1.0000 17.250 1.1240 0.05895 0.05416 0.0574 0.0113 1.0000 17.500 1.1204 0.06235 0.05768 0.0569 0.0112 1.0000 17.750 1.1148 0.06618 0.06164 0.0560 0.0111 1.0000 18.000 1.1089 0.07020 0.06579 0.0548 0.0111 1.0000 18.250 1.1017 0.07462 0.07034 0.0532 0.0110 1.0000 18.500 1.0897 0.07993 0.07580 0.0511 0.0110 1.0000 18.750 1.0802 0.08511 0.08111 0.0486 0.0109 1.0000 19.000 1.0677 0.09099 0.08713 0.0456 0.0109 1.0000 19.250 1.0514 0.09777 0.09406 0.0421 0.0108 1.0000