XFOIL Version 6.96 Calculated polar for: EPPLER 635 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 ------ -------- --------- --------- -------- -------- -------- -9.250 -0.5030 0.08714 0.08517 -0.0022 1.0000 0.0172 -9.000 -0.5134 0.08080 0.07884 -0.0084 1.0000 0.0172 -8.750 -0.5257 0.07588 0.07388 -0.0105 1.0000 0.0173 -8.500 -0.5385 0.07183 0.06978 -0.0100 1.0000 0.0173 -8.250 -0.5478 0.06801 0.06590 -0.0087 1.0000 0.0173 -8.000 -0.5534 0.06366 0.06143 -0.0076 1.0000 0.0173 -7.750 -0.5580 0.05772 0.05522 -0.0086 0.8630 0.0178 -7.500 -0.5576 0.05557 0.05277 -0.0061 0.8025 0.0180 -7.250 -0.5522 0.05354 0.05054 -0.0044 0.7675 0.0183 -7.000 -0.5460 0.05076 0.04753 -0.0026 0.7420 0.0186 -6.750 -0.5372 0.04827 0.04484 -0.0010 0.7195 0.0192 -6.500 -0.5278 0.04528 0.04160 0.0010 0.7008 0.0202 -6.250 -0.5120 0.04206 0.03784 0.0044 0.6845 0.0224 -6.000 -0.5151 0.03595 0.03126 0.0082 0.6722 0.0232 -5.750 -0.4980 0.03428 0.02953 0.0091 0.6552 0.0238 -5.500 -0.4805 0.03282 0.02793 0.0104 0.6400 0.0246 -4.500 -0.4074 0.02147 0.01472 0.0206 0.5913 0.0229 -4.250 -0.3818 0.02076 0.01382 0.0215 0.5787 0.0225 -4.000 -0.3570 0.01827 0.01100 0.0225 0.5675 0.0229 -3.750 -0.3296 0.01626 0.00880 0.0229 0.5563 0.0235 -3.500 -0.3025 0.01517 0.00760 0.0233 0.5452 0.0241 -3.250 -0.2761 0.01443 0.00677 0.0238 0.5344 0.0249 -3.000 -0.2501 0.01385 0.00612 0.0243 0.5238 0.0260 -2.750 -0.2242 0.01339 0.00560 0.0249 0.5143 0.0275 -2.250 -0.1738 0.01254 0.00458 0.0264 0.4957 0.0291 -2.000 -0.1507 0.01197 0.00392 0.0276 0.4874 0.0303 -1.750 -0.1266 0.01157 0.00348 0.0285 0.4790 0.0325 -1.500 -0.1012 0.01135 0.00321 0.0292 0.4714 0.0351 -1.250 -0.0755 0.01116 0.00296 0.0298 0.4636 0.0373 -1.000 -0.0502 0.01094 0.00270 0.0305 0.4563 0.0436 -0.750 -0.0273 0.01047 0.00250 0.0316 0.4491 0.1202 -0.500 -0.0380 0.00805 0.00214 0.0388 0.4453 0.6816 -0.250 0.0500 0.00825 0.00306 0.0276 0.4345 0.9332 0.000 0.1007 0.00895 0.00361 0.0236 0.4268 0.9469 0.250 0.1689 0.00981 0.00432 0.0160 0.4179 0.9604 0.500 0.2312 0.01036 0.00476 0.0094 0.4102 0.9719 0.750 0.2714 0.01033 0.00463 0.0068 0.4035 0.9738 1.000 0.3057 0.01033 0.00456 0.0054 0.3980 0.9757 1.250 0.3386 0.01031 0.00450 0.0043 0.3926 0.9781 1.500 0.3689 0.01038 0.00448 0.0036 0.3875 0.9811 1.750 0.3982 0.01044 0.00450 0.0033 0.3825 0.9840 2.000 0.4328 0.01034 0.00438 0.0017 0.3773 0.9854 2.250 0.4662 0.01033 0.00430 0.0004 0.3724 0.9871 2.500 0.4987 0.01032 0.00426 -0.0007 0.3679 0.9890 2.750 0.5302 0.01029 0.00423 -0.0016 0.3631 0.9912 3.000 0.5608 0.01035 0.00424 -0.0024 0.3584 0.9934 3.250 0.5931 0.01034 0.00421 -0.0035 0.3541 0.9950 3.500 0.6257 0.01028 0.00416 -0.0047 0.3497 0.9965 3.750 0.6583 0.01026 0.00412 -0.0058 0.3454 0.9983 4.000 0.6907 0.01032 0.00413 -0.0071 0.3409 0.9999 4.250 0.7156 0.01033 0.00419 -0.0066 0.3368 1.0000 4.500 0.7399 0.01039 0.00427 -0.0061 0.3330 1.0000 4.750 0.7639 0.01050 0.00436 -0.0055 0.3291 1.0000 5.000 0.7879 0.01063 0.00449 -0.0049 0.3252 1.0000 5.250 0.8123 0.01068 0.00459 -0.0044 0.3211 1.0000 5.500 0.8365 0.01077 0.00470 -0.0038 0.3167 1.0000 5.750 0.8601 0.01096 0.00484 -0.0032 0.3122 1.0000 6.000 0.8845 0.01099 0.00496 -0.0027 0.3078 1.0000 6.250 0.9087 0.01107 0.00508 -0.0022 0.3030 1.0000 6.500 0.9324 0.01125 0.00524 -0.0016 0.2985 1.0000 6.750 0.9565 0.01134 0.00540 -0.0010 0.2940 1.0000 7.000 0.9805 0.01143 0.00555 -0.0005 0.2890 1.0000 7.250 1.0039 0.01162 0.00572 0.0001 0.2840 1.0000 7.500 1.0279 0.01173 0.00592 0.0007 0.2792 1.0000 7.750 1.0517 0.01184 0.00608 0.0013 0.2737 1.0000 8.000 1.0747 0.01206 0.00629 0.0019 0.2683 1.0000 8.250 1.0986 0.01215 0.00650 0.0025 0.2625 1.0000 8.500 1.1214 0.01236 0.00671 0.0031 0.2560 1.0000 8.750 1.1449 0.01250 0.00694 0.0037 0.2491 1.0000 9.000 1.1672 0.01274 0.00718 0.0044 0.2416 1.0000 9.250 1.1902 0.01292 0.00745 0.0051 0.2337 1.0000 9.500 1.2119 0.01320 0.00776 0.0058 0.2250 1.0000 9.750 1.2337 0.01348 0.00808 0.0066 0.2152 1.0000 10.000 1.2544 0.01383 0.00844 0.0075 0.2020 1.0000 10.250 1.2735 0.01433 0.00891 0.0085 0.1859 1.0000 10.500 1.2916 0.01491 0.00946 0.0096 0.1663 1.0000 10.750 1.3064 0.01573 0.01018 0.0111 0.1449 1.0000 11.000 1.3194 0.01665 0.01102 0.0128 0.1243 1.0000 11.250 1.3300 0.01767 0.01197 0.0148 0.1076 1.0000 11.500 1.3395 0.01867 0.01293 0.0169 0.0934 1.0000 11.750 1.3470 0.01971 0.01394 0.0192 0.0817 1.0000 12.000 1.3527 0.02074 0.01498 0.0218 0.0720 1.0000 12.250 1.3564 0.02178 0.01606 0.0246 0.0647 1.0000 12.500 1.3493 0.02296 0.01726 0.0289 0.0598 1.0000 12.750 1.3382 0.02428 0.01865 0.0331 0.0562 1.0000 13.000 1.3274 0.02647 0.02090 0.0351 0.0519 1.0000 13.250 1.3183 0.02925 0.02374 0.0358 0.0485 1.0000 13.500 1.3131 0.03201 0.02659 0.0359 0.0451 1.0000 13.750 1.3029 0.03548 0.03012 0.0357 0.0415 1.0000 14.000 1.2910 0.03926 0.03398 0.0353 0.0391 1.0000 14.250 1.2816 0.04283 0.03762 0.0349 0.0358 1.0000 14.500 1.2701 0.04671 0.04158 0.0343 0.0340 1.0000 14.750 1.2538 0.05121 0.04613 0.0334 0.0314 1.0000 15.000 1.2425 0.05519 0.05020 0.0327 0.0298 1.0000 15.250 1.2269 0.05976 0.05483 0.0316 0.0263 1.0000 15.500 1.2145 0.06414 0.05928 0.0305 0.0252 1.0000 15.750 1.1977 0.06926 0.06443 0.0290 0.0207 1.0000 16.000 1.1824 0.07435 0.06955 0.0274 0.0186 1.0000 16.250 1.1709 0.07901 0.07429 0.0260 0.0168 1.0000 16.500 1.1575 0.08406 0.07939 0.0243 0.0151 1.0000