XFOIL Version 6.96 Calculated polar for: EPPLER 329 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 ------ -------- --------- --------- -------- -------- -------- -9.750 -0.1838 0.07743 0.07488 -0.0562 0.8339 0.0118 -9.250 -0.3449 0.08360 0.08143 -0.0410 0.9867 0.0110 -9.000 -0.3144 0.07622 0.07399 -0.0541 0.9291 0.0112 -8.750 -0.2782 0.06532 0.06268 -0.0756 0.8495 0.0113 -8.500 -0.2969 0.06091 0.05798 -0.0753 0.8001 0.0111 -8.250 -0.3111 0.05783 0.05467 -0.0726 0.7677 0.0111 -7.750 -0.3151 0.05201 0.04845 -0.0688 0.7236 0.0110 -7.250 -0.3256 0.04469 0.04076 -0.0640 0.6931 0.0086 -7.000 -0.3171 0.04312 0.03904 -0.0625 0.6773 0.0088 -6.500 -0.3182 0.03034 0.02536 -0.0544 0.6578 0.0061 -6.250 -0.3083 0.02703 0.02169 -0.0518 0.6457 0.0060 -6.000 -0.2948 0.02401 0.01826 -0.0495 0.6349 0.0059 -5.750 -0.2779 0.02133 0.01514 -0.0474 0.6242 0.0058 -5.500 -0.2573 0.01928 0.01271 -0.0460 0.6136 0.0058 -5.250 -0.2347 0.01770 0.01079 -0.0448 0.6029 0.0058 -5.000 -0.2110 0.01640 0.00919 -0.0438 0.5917 0.0058 -4.750 -0.1865 0.01559 0.00821 -0.0431 0.5809 0.0058 -4.500 -0.1623 0.01483 0.00727 -0.0423 0.5710 0.0059 -4.250 -0.1381 0.01423 0.00655 -0.0415 0.5615 0.0060 -4.000 -0.1140 0.01371 0.00592 -0.0407 0.5526 0.0061 -3.750 -0.0909 0.01314 0.00525 -0.0397 0.5429 0.0064 -3.500 -0.0668 0.01278 0.00482 -0.0390 0.5339 0.0065 -3.000 -0.0178 0.01221 0.00413 -0.0376 0.5174 0.0073 -2.500 0.0318 0.01173 0.00352 -0.0364 0.5020 0.0087 -2.250 0.0567 0.01156 0.00329 -0.0358 0.4938 0.0098 -2.000 0.0821 0.01137 0.00308 -0.0352 0.4867 0.0120 -1.750 0.1075 0.01123 0.00291 -0.0347 0.4798 0.0168 -1.500 0.1328 0.01106 0.00276 -0.0342 0.4735 0.0259 -1.250 0.1576 0.01085 0.00264 -0.0337 0.4666 0.0544 -1.000 0.1819 0.01063 0.00254 -0.0331 0.4602 0.1015 -0.750 0.1972 0.00950 0.00233 -0.0314 0.4548 0.3878 -0.500 0.2011 0.00822 0.00247 -0.0266 0.4501 0.7957 -0.250 0.2260 0.00839 0.00261 -0.0256 0.4447 0.8231 0.000 0.2517 0.00854 0.00273 -0.0248 0.4391 0.8383 0.250 0.2775 0.00868 0.00281 -0.0242 0.4332 0.8483 0.500 0.3027 0.00887 0.00293 -0.0234 0.4282 0.8598 0.750 0.3285 0.00898 0.00303 -0.0227 0.4234 0.8657 1.000 0.3561 0.00903 0.00301 -0.0227 0.4182 0.8669 1.250 0.3833 0.00910 0.00300 -0.0226 0.4132 0.8681 1.500 0.4111 0.00915 0.00301 -0.0226 0.4085 0.8696 1.750 0.4386 0.00921 0.00301 -0.0226 0.4038 0.8710 2.000 0.4658 0.00929 0.00303 -0.0226 0.3991 0.8723 2.250 0.4935 0.00935 0.00305 -0.0227 0.3948 0.8735 2.500 0.5211 0.00941 0.00308 -0.0228 0.3904 0.8747 2.750 0.5484 0.00950 0.00312 -0.0228 0.3861 0.8759 3.000 0.5752 0.00959 0.00317 -0.0227 0.3819 0.8771 3.250 0.6025 0.00965 0.00324 -0.0226 0.3778 0.8783 3.500 0.6295 0.00973 0.00331 -0.0226 0.3737 0.8795 3.750 0.6561 0.00984 0.00339 -0.0225 0.3695 0.8806 4.000 0.6828 0.00994 0.00348 -0.0224 0.3656 0.8818 4.250 0.7099 0.01002 0.00357 -0.0224 0.3615 0.8831 4.500 0.7366 0.01012 0.00367 -0.0223 0.3572 0.8845 4.750 0.7628 0.01025 0.00378 -0.0222 0.3531 0.8859 5.000 0.7895 0.01036 0.00389 -0.0221 0.3493 0.8874 5.250 0.8162 0.01046 0.00400 -0.0221 0.3449 0.8890 5.500 0.8424 0.01059 0.00414 -0.0220 0.3405 0.8907 5.750 0.8681 0.01074 0.00428 -0.0218 0.3363 0.8923 6.000 0.8943 0.01083 0.00441 -0.0216 0.3318 0.8937 6.250 0.9199 0.01096 0.00457 -0.0214 0.3270 0.8951 6.500 0.9448 0.01112 0.00474 -0.0211 0.3226 0.8967 6.750 0.9704 0.01125 0.00490 -0.0209 0.3178 0.8984 7.000 0.9957 0.01139 0.00508 -0.0206 0.3124 0.9002 7.250 1.0198 0.01159 0.00527 -0.0202 0.3071 0.9022 7.500 1.0452 0.01173 0.00546 -0.0200 0.3015 0.9042 7.750 1.0693 0.01192 0.00567 -0.0196 0.2947 0.9063 8.000 1.0933 0.01210 0.00588 -0.0191 0.2886 0.9083 8.250 1.1163 0.01229 0.00611 -0.0185 0.2815 0.9107 8.500 1.1387 0.01251 0.00636 -0.0178 0.2742 0.9134 8.750 1.1609 0.01274 0.00662 -0.0170 0.2665 0.9163 9.000 1.1828 0.01299 0.00690 -0.0163 0.2588 0.9193 9.500 1.2234 0.01356 0.00752 -0.0143 0.2404 0.9258 9.750 1.2417 0.01390 0.00786 -0.0129 0.2303 0.9300 10.000 1.2586 0.01428 0.00825 -0.0114 0.2203 0.9350 10.250 1.2736 0.01466 0.00865 -0.0095 0.2090 0.9409 10.500 1.2878 0.01509 0.00910 -0.0075 0.1974 0.9492 10.750 1.3041 0.01565 0.00965 -0.0062 0.1844 0.9590 11.000 1.3252 0.01633 0.01033 -0.0062 0.1709 0.9708 11.500 1.3540 0.01789 0.01185 -0.0040 0.1450 1.0000 11.750 1.3621 0.01877 0.01271 -0.0019 0.1340 1.0000 12.000 1.3693 0.01972 0.01366 0.0002 0.1251 1.0000 12.250 1.3733 0.02091 0.01484 0.0023 0.1151 1.0000 12.500 1.3791 0.02209 0.01605 0.0040 0.1071 1.0000 12.750 1.3823 0.02355 0.01753 0.0056 0.0995 1.0000 13.250 1.3861 0.02708 0.02112 0.0079 0.0858 1.0000 13.500 1.3851 0.02930 0.02337 0.0087 0.0802 1.0000 13.750 1.3858 0.03154 0.02566 0.0092 0.0743 1.0000 14.000 1.3825 0.03425 0.02841 0.0095 0.0696 1.0000 14.250 1.3825 0.03675 0.03099 0.0096 0.0657 1.0000 14.500 1.3769 0.03990 0.03418 0.0096 0.0611 1.0000 14.750 1.3733 0.04293 0.03730 0.0094 0.0580 1.0000 15.000 1.3677 0.04623 0.04066 0.0091 0.0541 1.0000 15.500 1.3548 0.05329 0.04785 0.0081 0.0486 1.0000 15.750 1.3473 0.05707 0.05170 0.0073 0.0455 1.0000 16.000 1.3382 0.06117 0.05586 0.0064 0.0430 1.0000 16.250 1.3331 0.06487 0.05965 0.0055 0.0409 1.0000 16.500 1.3261 0.06886 0.06370 0.0044 0.0385 1.0000 16.750 1.3170 0.07324 0.06815 0.0032 0.0362 1.0000 17.000 1.3118 0.07717 0.07216 0.0020 0.0349 1.0000 17.250 1.3057 0.08127 0.07634 0.0007 0.0325 1.0000 17.500 1.2983 0.08565 0.08078 -0.0008 0.0308 1.0000