XFOIL Version 6.96 Calculated polar for: EPPLER 331 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 ------ -------- --------- --------- -------- -------- -------- -9.000 -0.4658 0.08875 0.08663 -0.0070 1.0000 0.0083 -8.750 -0.4690 0.08430 0.08221 -0.0098 1.0000 0.0083 -8.500 -0.4760 0.07957 0.07750 -0.0138 1.0000 0.0080 -8.250 -0.4724 0.07285 0.07068 -0.0223 0.9035 0.0080 -8.000 -0.4835 0.06968 0.06712 -0.0215 0.8065 0.0079 -7.750 -0.4934 0.06649 0.06373 -0.0200 0.7716 0.0079 -7.500 -0.4989 0.06271 0.05977 -0.0188 0.7454 0.0078 -7.000 -0.5034 0.05374 0.05037 -0.0154 0.7093 0.0062 -6.500 -0.5052 0.04154 0.03749 -0.0088 0.6833 0.0046 -6.250 -0.4967 0.03789 0.03355 -0.0062 0.6694 0.0045 -6.000 -0.4871 0.03390 0.02923 -0.0034 0.6566 0.0044 -5.750 -0.4809 0.02743 0.02217 0.0012 0.6465 0.0045 -5.500 -0.4691 0.02169 0.01558 0.0053 0.6356 0.0046 -5.250 -0.4488 0.01957 0.01307 0.0068 0.6229 0.0048 -5.000 -0.4253 0.01856 0.01184 0.0077 0.6098 0.0050 -4.750 -0.4008 0.01751 0.01055 0.0085 0.5969 0.0052 -4.500 -0.3757 0.01661 0.00943 0.0092 0.5839 0.0054 -4.250 -0.3502 0.01577 0.00841 0.0098 0.5722 0.0056 -4.000 -0.3245 0.01510 0.00758 0.0104 0.5615 0.0060 -3.750 -0.2990 0.01447 0.00678 0.0111 0.5502 0.0063 -3.500 -0.2733 0.01400 0.00617 0.0116 0.5388 0.0069 -3.250 -0.2489 0.01339 0.00549 0.0124 0.5288 0.0071 -2.750 -0.1998 0.01246 0.00441 0.0139 0.5096 0.0074 -2.500 -0.1752 0.01210 0.00398 0.0147 0.5001 0.0076 -2.250 -0.1502 0.01180 0.00361 0.0154 0.4907 0.0079 -2.000 -0.1251 0.01152 0.00326 0.0161 0.4828 0.0085 -1.750 -0.0997 0.01131 0.00296 0.0167 0.4742 0.0092 -1.500 -0.0742 0.01108 0.00268 0.0173 0.4659 0.0109 -1.250 -0.0489 0.01090 0.00245 0.0179 0.4579 0.0157 -1.000 -0.0248 0.01056 0.00229 0.0186 0.4509 0.0595 -0.750 -0.0020 0.01015 0.00216 0.0195 0.4435 0.1499 -0.500 -0.0138 0.00769 0.00179 0.0269 0.4395 0.7104 -0.250 0.0106 0.00776 0.00245 0.0290 0.4321 0.9013 0.250 0.0668 0.00833 0.00286 0.0300 0.4188 0.9286 0.750 0.1374 0.00897 0.00332 0.0276 0.4045 0.9428 1.000 0.1714 0.00906 0.00332 0.0263 0.3981 0.9437 1.250 0.2021 0.00911 0.00330 0.0257 0.3924 0.9444 1.500 0.2327 0.00916 0.00329 0.0251 0.3860 0.9452 1.750 0.2628 0.00923 0.00328 0.0245 0.3802 0.9459 2.000 0.2926 0.00926 0.00328 0.0241 0.3749 0.9467 2.250 0.3216 0.00932 0.00328 0.0237 0.3689 0.9477 2.500 0.3501 0.00939 0.00330 0.0235 0.3638 0.9487 2.750 0.3776 0.00943 0.00332 0.0235 0.3589 0.9499 3.000 0.4042 0.00949 0.00335 0.0237 0.3535 0.9513 3.250 0.4282 0.00955 0.00338 0.0244 0.3486 0.9531 3.500 0.4422 0.00955 0.00338 0.0273 0.3446 0.9565 4.000 0.4981 0.00971 0.00349 0.0270 0.3342 0.9582 4.250 0.5276 0.00977 0.00356 0.0265 0.3291 0.9587 4.500 0.5567 0.00986 0.00364 0.0261 0.3235 0.9592 4.750 0.5855 0.00996 0.00373 0.0257 0.3183 0.9598 5.000 0.6143 0.01004 0.00382 0.0253 0.3126 0.9604 5.250 0.6424 0.01015 0.00392 0.0250 0.3067 0.9611 5.500 0.6708 0.01026 0.00405 0.0247 0.3011 0.9619 5.750 0.6991 0.01037 0.00418 0.0244 0.2951 0.9629 6.000 0.7261 0.01051 0.00431 0.0243 0.2889 0.9640 6.250 0.7526 0.01061 0.00445 0.0244 0.2826 0.9651 6.500 0.7774 0.01076 0.00460 0.0248 0.2759 0.9664 6.750 0.8012 0.01088 0.00475 0.0254 0.2686 0.9680 7.000 0.8177 0.01102 0.00490 0.0276 0.2622 0.9708 7.250 0.8451 0.01118 0.00509 0.0274 0.2543 0.9715 7.500 0.8736 0.01140 0.00530 0.0268 0.2447 0.9720 7.750 0.9024 0.01161 0.00554 0.0262 0.2350 0.9727 8.000 0.9308 0.01185 0.00579 0.0257 0.2245 0.9734 8.250 0.9585 0.01212 0.00607 0.0252 0.2137 0.9742 8.500 0.9849 0.01244 0.00639 0.0250 0.2007 0.9752 8.750 1.0104 0.01279 0.00673 0.0249 0.1877 0.9763 9.000 1.0349 0.01320 0.00712 0.0250 0.1724 0.9776 9.250 1.0580 0.01364 0.00754 0.0253 0.1572 0.9792 9.500 1.0788 0.01414 0.00801 0.0259 0.1418 0.9812 9.750 1.0973 0.01467 0.00852 0.0271 0.1274 0.9835 10.000 1.1217 0.01536 0.00916 0.0266 0.1104 0.9845 10.250 1.1455 0.01606 0.00983 0.0263 0.0954 0.9856 10.500 1.1685 0.01677 0.01053 0.0261 0.0828 0.9870 10.750 1.1904 0.01752 0.01128 0.0261 0.0715 0.9889 11.000 1.2109 0.01832 0.01208 0.0262 0.0619 0.9911 11.250 1.2286 0.01916 0.01293 0.0267 0.0533 0.9936 11.500 1.2491 0.02007 0.01387 0.0265 0.0455 0.9955 11.750 1.2672 0.02117 0.01497 0.0263 0.0373 0.9981 12.000 1.2724 0.02211 0.01594 0.0286 0.0323 1.0000 12.250 1.2545 0.02289 0.01676 0.0352 0.0302 1.0000 12.500 1.2484 0.02392 0.01788 0.0390 0.0298 1.0000 12.750 1.2430 0.02551 0.01952 0.0414 0.0266 1.0000 13.000 1.2377 0.02762 0.02167 0.0427 0.0235 1.0000 13.250 1.2325 0.03013 0.02421 0.0433 0.0196 1.0000 13.500 1.2356 0.03210 0.02633 0.0436 0.0206 1.0000 13.750 1.2300 0.03508 0.02936 0.0434 0.0179 1.0000 14.000 1.2249 0.03814 0.03249 0.0431 0.0160 1.0000 14.250 1.2192 0.04135 0.03577 0.0426 0.0145 1.0000 14.500 1.2119 0.04482 0.03931 0.0419 0.0129 1.0000 14.750 1.2081 0.04796 0.04257 0.0413 0.0132 1.0000 15.000 1.1993 0.05172 0.04641 0.0405 0.0123 1.0000 15.250 1.1918 0.05539 0.05017 0.0396 0.0118 1.0000 15.500 1.1845 0.05911 0.05400 0.0386 0.0116 1.0000 15.750 1.1760 0.06314 0.05812 0.0374 0.0108 1.0000 16.000 1.1656 0.06752 0.06254 0.0359 0.0091 1.0000 16.250 1.1584 0.07159 0.06671 0.0346 0.0088 1.0000 16.500 1.1511 0.07577 0.07097 0.0331 0.0083 1.0000 16.750 1.1423 0.08024 0.07552 0.0315 0.0077 1.0000 17.000 1.1339 0.08473 0.08009 0.0298 0.0071 1.0000 17.250 1.1271 0.08909 0.08456 0.0281 0.0074 1.0000 17.500 1.1200 0.09354 0.08909 0.0264 0.0068 1.0000 17.750 1.1120 0.09822 0.09386 0.0245 0.0063 1.0000 18.000 1.1047 0.10289 0.09861 0.0225 0.0060 1.0000