XFOIL Version 6.96 Calculated polar for: EPPLER 330 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5466 0.08600 0.08397 0.0006 1.0000 0.0124 -8.750 -0.5586 0.08030 0.07828 -0.0042 1.0000 0.0123 -8.500 -0.5714 0.07578 0.07372 -0.0055 1.0000 0.0123 -8.250 -0.5826 0.07231 0.07022 -0.0047 1.0000 0.0124 -8.000 -0.5912 0.06899 0.06684 -0.0033 1.0000 0.0124 -7.750 -0.5936 0.06572 0.06350 -0.0023 1.0000 0.0126 -7.500 -0.5939 0.06233 0.06004 -0.0011 1.0000 0.0127 -7.250 -0.5917 0.05905 0.05667 0.0002 1.0000 0.0130 -7.000 -0.5878 0.05572 0.05324 0.0018 1.0000 0.0133 -6.750 -0.5818 0.05245 0.04984 0.0035 1.0000 0.0136 -6.500 -0.5738 0.04927 0.04653 0.0053 1.0000 0.0140 -6.250 -0.5506 0.04505 0.04206 0.0043 0.9294 0.0148 -6.000 -0.5293 0.04228 0.03874 0.0071 0.8489 0.0164 -5.750 -0.5174 0.04036 0.03637 0.0104 0.8080 0.0166 -5.500 -0.5063 0.03802 0.03362 0.0134 0.7784 0.0167 -3.750 -0.3770 0.01840 0.01146 0.0280 0.6484 0.0118 -3.500 -0.3485 0.01600 0.00886 0.0284 0.6337 0.0104 -3.250 -0.3211 0.01458 0.00724 0.0291 0.6193 0.0101 -3.000 -0.2956 0.01367 0.00617 0.0299 0.6054 0.0101 -2.500 -0.2466 0.01252 0.00480 0.0318 0.5787 0.0116 -2.250 -0.2248 0.01174 0.00395 0.0332 0.5666 0.0133 -2.000 -0.2001 0.01143 0.00357 0.0340 0.5544 0.0150 -1.750 -0.1757 0.01111 0.00318 0.0349 0.5430 0.0207 -1.500 -0.1563 0.01025 0.00271 0.0367 0.5328 0.1302 -1.250 -0.1471 0.00879 0.00236 0.0399 0.5233 0.4324 -1.000 -0.1424 0.00739 0.00272 0.0456 0.5152 0.8816 -0.750 -0.1026 0.00840 0.00361 0.0446 0.5037 0.9201 -0.500 -0.0207 0.00967 0.00467 0.0345 0.4890 0.9332 -0.250 0.0326 0.01022 0.00508 0.0298 0.4770 0.9403 0.000 0.0758 0.01052 0.00526 0.0269 0.4668 0.9462 0.250 0.1179 0.01066 0.00528 0.0240 0.4574 0.9487 0.500 0.1526 0.01074 0.00526 0.0226 0.4479 0.9517 0.750 0.1756 0.01087 0.00534 0.0237 0.4407 0.9570 1.000 0.2082 0.01088 0.00526 0.0226 0.4327 0.9592 1.250 0.2445 0.01085 0.00517 0.0208 0.4244 0.9605 1.500 0.2786 0.01086 0.00510 0.0194 0.4170 0.9620 1.750 0.3124 0.01085 0.00506 0.0180 0.4097 0.9641 2.000 0.3439 0.01092 0.00505 0.0172 0.4025 0.9668 2.250 0.3689 0.01103 0.00516 0.0177 0.3961 0.9710 2.500 0.3983 0.01104 0.00512 0.0172 0.3897 0.9729 2.750 0.4325 0.01097 0.00503 0.0157 0.3829 0.9740 3.000 0.4700 0.01094 0.00497 0.0136 0.3759 0.9761 3.250 0.5058 0.01094 0.00495 0.0118 0.3692 0.9791 3.500 0.5358 0.01098 0.00498 0.0111 0.3629 0.9818 3.750 0.5606 0.01112 0.00510 0.0116 0.3570 0.9840 4.000 0.5900 0.01109 0.00509 0.0111 0.3506 0.9853 4.500 0.6520 0.01102 0.00502 0.0093 0.3377 0.9873 4.750 0.6818 0.01106 0.00504 0.0086 0.3312 0.9884 5.000 0.7106 0.01107 0.00509 0.0082 0.3249 0.9895 5.250 0.7393 0.01111 0.00513 0.0078 0.3181 0.9908 5.500 0.7676 0.01116 0.00523 0.0074 0.3115 0.9921 5.750 0.7948 0.01123 0.00531 0.0073 0.3042 0.9931 6.000 0.8214 0.01131 0.00542 0.0073 0.2970 0.9941 6.250 0.8501 0.01139 0.00552 0.0069 0.2894 0.9952 6.500 0.8800 0.01141 0.00560 0.0061 0.2813 0.9961 6.750 0.9079 0.01152 0.00570 0.0058 0.2725 0.9969 7.000 0.9357 0.01158 0.00583 0.0055 0.2636 0.9976 7.250 0.9637 0.01170 0.00597 0.0051 0.2541 0.9985 7.500 0.9924 0.01185 0.00614 0.0045 0.2434 0.9995 7.750 1.0189 0.01204 0.00634 0.0044 0.2318 1.0000 8.000 1.0421 0.01226 0.00659 0.0050 0.2193 1.0000 8.250 1.0649 0.01252 0.00687 0.0056 0.2069 1.0000 8.500 1.0871 0.01284 0.00719 0.0062 0.1930 1.0000 8.750 1.1086 0.01324 0.00759 0.0069 0.1769 1.0000 9.000 1.1296 0.01369 0.00801 0.0077 0.1575 1.0000 9.250 1.1493 0.01427 0.00853 0.0086 0.1388 1.0000 9.500 1.1683 0.01488 0.00910 0.0096 0.1204 1.0000 9.750 1.1865 0.01555 0.00973 0.0107 0.1038 1.0000 10.000 1.2031 0.01632 0.01045 0.0120 0.0880 1.0000 10.250 1.2187 0.01712 0.01122 0.0134 0.0746 1.0000 10.750 1.2465 0.01876 0.01288 0.0167 0.0539 1.0000 11.000 1.2587 0.01957 0.01372 0.0186 0.0462 1.0000 11.250 1.2676 0.02053 0.01470 0.0209 0.0396 1.0000 11.500 1.2741 0.02150 0.01569 0.0235 0.0342 1.0000 11.750 1.2776 0.02248 0.01674 0.0266 0.0305 1.0000 12.000 1.2784 0.02341 0.01773 0.0300 0.0276 1.0000 12.250 1.2658 0.02447 0.01884 0.0354 0.0256 1.0000 12.500 1.2402 0.02554 0.01999 0.0424 0.0250 1.0000 12.750 1.2172 0.02743 0.02195 0.0470 0.0239 1.0000 13.000 1.2067 0.02941 0.02403 0.0493 0.0233 1.0000 13.250 1.2003 0.03161 0.02634 0.0505 0.0221 1.0000 13.500 1.1934 0.03428 0.02909 0.0511 0.0208 1.0000 13.750 1.1851 0.03739 0.03228 0.0511 0.0197 1.0000 14.000 1.1709 0.04139 0.03635 0.0506 0.0184 1.0000 14.250 1.1574 0.04548 0.04053 0.0499 0.0177 1.0000 14.500 1.1469 0.04933 0.04449 0.0491 0.0169 1.0000 14.750 1.1472 0.05196 0.04720 0.0486 0.0154 1.0000 15.000 1.1312 0.05663 0.05200 0.0474 0.0156 1.0000 15.250 1.1271 0.05993 0.05534 0.0465 0.0139 1.0000 15.500 1.1154 0.06435 0.05983 0.0451 0.0135 1.0000 15.750 1.1036 0.06894 0.06449 0.0435 0.0129 1.0000 16.000 1.0856 0.07457 0.07022 0.0415 0.0124 1.0000 16.250 1.0730 0.07954 0.07528 0.0397 0.0118 1.0000 16.500 1.0763 0.08233 0.07814 0.0387 0.0105 1.0000 16.750 1.0628 0.08762 0.08354 0.0367 0.0107 1.0000 17.000 1.0586 0.09168 0.08763 0.0350 0.0093 1.0000 17.250 1.0473 0.09684 0.09288 0.0330 0.0092 1.0000 17.500 1.0328 0.10266 0.09877 0.0306 0.0089 1.0000 17.750 1.0189 0.10848 0.10466 0.0281 0.0079 1.0000