XFOIL Version 6.94 Calculated polar for: EPPLER 593 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.300 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.3034 0.01377 0.00612 -0.0345 0.4763 0.3231 0.500 0.3888 0.01252 0.00657 -0.0402 0.4716 1.0000 1.000 0.4422 0.01281 0.00676 -0.0395 0.4688 1.0000 1.500 0.4955 0.01321 0.00708 -0.0388 0.4652 1.0000 2.000 0.5490 0.01364 0.00744 -0.0383 0.4613 1.0000 2.500 0.6026 0.01396 0.00769 -0.0376 0.4571 1.0000 3.000 0.6564 0.01438 0.00803 -0.0371 0.4538 1.0000 3.500 0.7097 0.01509 0.00865 -0.0366 0.4501 1.0000 4.000 0.7629 0.01573 0.00938 -0.0363 0.4461 1.0000 4.500 0.8166 0.01619 0.00994 -0.0361 0.4410 1.0000 5.000 0.8705 0.01650 0.01029 -0.0357 0.4358 1.0000 5.500 0.9251 0.01661 0.01039 -0.0352 0.4313 1.0000 6.000 0.9787 0.01724 0.01097 -0.0348 0.4261 1.0000 6.500 1.0318 0.01742 0.01138 -0.0345 0.4199 1.0000 7.000 1.0860 0.01736 0.01143 -0.0341 0.4129 1.0000 7.500 1.1423 0.01701 0.01104 -0.0336 0.4071 1.0000 8.000 1.1948 0.01724 0.01146 -0.0332 0.3994 1.0000 8.500 1.2495 0.01681 0.01118 -0.0327 0.3896 1.0000 9.000 1.3044 0.01644 0.01086 -0.0322 0.3802 1.0000 9.500 1.3571 0.01613 0.01078 -0.0317 0.3663 1.0000 10.000 1.4088 0.01601 0.01086 -0.0311 0.3479 1.0000 10.500 1.4575 0.01616 0.01108 -0.0302 0.3203 1.0000 11.000 1.4958 0.01729 0.01215 -0.0287 0.2739 1.0000 11.500 1.5144 0.01985 0.01455 -0.0257 0.2233 1.0000 12.000 1.5017 0.02350 0.01817 -0.0201 0.1923 1.0000 12.500 1.4618 0.03099 0.02575 -0.0188 0.1752 1.0000 13.000 1.4287 0.03885 0.03363 -0.0186 0.1576 1.0000 13.500 1.4006 0.04636 0.04113 -0.0187 0.1410 1.0000 14.000 1.3786 0.05356 0.04833 -0.0192 0.1249 1.0000 14.500 1.3643 0.06069 0.05548 -0.0203 0.1092 1.0000 15.000 1.3540 0.06781 0.06262 -0.0218 0.0950 1.0000 15.500 1.3453 0.07511 0.06993 -0.0236 0.0823 1.0000 16.000 1.3367 0.08277 0.07762 -0.0258 0.0716 1.0000 16.500 1.3286 0.09065 0.08553 -0.0283 0.0622 1.0000 17.000 1.3228 0.09848 0.09340 -0.0310 0.0540 1.0000 17.500 1.3174 0.10660 0.10162 -0.0341 0.0470 1.0000 18.000 1.3130 0.11469 0.10981 -0.0374 0.0410 1.0000 18.500 1.3090 0.12296 0.11816 -0.0410 0.0359 1.0000 19.000 1.3058 0.13118 0.12646 -0.0450 0.0316 1.0000 19.500 1.3030 0.13958 0.13501 -0.0493 0.0278 1.0000 20.000 1.3001 0.14815 0.14376 -0.0539 0.0245 1.0000 20.500 1.2955 0.15710 0.15287 -0.0591 0.0216 1.0000 21.000 1.2919 0.16586 0.16174 -0.0645 0.0192 1.0000 21.500 1.2875 0.17503 0.17105 -0.0704 0.0170 1.0000 22.000 1.2820 0.18454 0.18077 -0.0766 0.0150 1.0000 22.500 1.2791 0.19334 0.18966 -0.0826 0.0133 1.0000 23.000 1.2723 0.20343 0.19995 -0.0896 0.0117 1.0000 23.500 1.2670 0.21306 0.20973 -0.0964 0.0104 1.0000 24.000 1.2603 0.22340 0.22023 -0.1037 0.0093 1.0000 24.500 1.2549 0.23339 0.23034 -0.1108 0.0083 1.0000 25.000 1.2347 0.24871 0.24596 -0.1210 0.0079 1.0000 26.000 1.1598 0.31646 0.31357 -0.1492 0.0145 1.0000 26.500 1.1739 0.32089 0.31805 -0.1526 0.0138 1.0000 27.000 1.1845 0.32804 0.32518 -0.1573 0.0135 1.0000 27.500 1.1943 0.33620 0.33332 -0.1628 0.0122 1.0000 28.000 1.2065 0.34122 0.33837 -0.1669 0.0114 1.0000 29.000 1.2281 0.35365 0.35080 -0.1760 0.0105 1.0000 29.500 1.2390 0.35946 0.35662 -0.1805 0.0096 1.0000 30.000 1.2498 0.36427 0.36145 -0.1848 0.0091 1.0000 30.500 1.2605 0.36800 0.36522 -0.1885 0.0087 1.0000 31.000 1.2702 0.37414 0.37136 -0.1933 0.0086 1.0000 31.500 1.2800 0.38064 0.37785 -0.1984 0.0080 1.0000 32.000 1.2896 0.38558 0.38282 -0.2028 0.0074 1.0000 32.500 1.2987 0.38993 0.38719 -0.2072 0.0070 1.0000 33.000 1.3069 0.39338 0.39068 -0.2112 0.0067 1.0000 33.500 1.3156 0.39927 0.39657 -0.2161 0.0064 1.0000 34.000 1.3246 0.40449 0.40180 -0.2207 0.0057 1.0000 34.500 1.3321 0.40860 0.40593 -0.2251 0.0052 1.0000 35.000 1.3393 0.41226 0.40963 -0.2296 0.0049 1.0000 36.000 1.3531 0.42094 0.41833 -0.2385 0.0046 1.0000 36.500 1.3604 0.42572 0.42314 -0.2431 0.0042 1.0000 37.000 1.3665 0.42966 0.42710 -0.2477 0.0039 1.0000 37.500 1.3720 0.43329 0.43076 -0.2521 0.0036 1.0000 38.000 1.3767 0.43637 0.43387 -0.2566 0.0034 1.0000 38.500 1.3809 0.43898 0.43651 -0.2611 0.0033 1.0000 39.500 1.3880 0.44417 0.44176 -0.2698 0.0031 1.0000 40.000 1.3927 0.44768 0.44528 -0.2747 0.0031 1.0000