XFOIL Version 6.94 Calculated polar for: EPPLER 598 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 0.3194 0.01094 0.00402 -0.0408 0.5298 0.4940 0.500 0.4239 0.00993 0.00401 -0.0499 0.5205 1.0000 1.000 0.4767 0.01007 0.00403 -0.0490 0.5121 1.0000 1.500 0.5294 0.01026 0.00402 -0.0481 0.5038 1.0000 2.000 0.5821 0.01060 0.00424 -0.0473 0.4959 1.0000 2.500 0.6353 0.01076 0.00436 -0.0466 0.4868 1.0000 3.000 0.6882 0.01103 0.00450 -0.0458 0.4788 1.0000 3.500 0.7412 0.01133 0.00479 -0.0452 0.4698 1.0000 4.000 0.7945 0.01153 0.00498 -0.0445 0.4608 1.0000 4.500 0.8475 0.01191 0.00527 -0.0439 0.4517 1.0000 5.000 0.9007 0.01211 0.00558 -0.0433 0.4419 1.0000 5.500 0.9538 0.01241 0.00579 -0.0427 0.4321 1.0000 6.000 1.0065 0.01269 0.00622 -0.0422 0.4215 1.0000 6.500 1.0592 0.01296 0.00646 -0.0416 0.4105 1.0000 7.000 1.1112 0.01328 0.00693 -0.0411 0.3981 1.0000 7.500 1.1627 0.01364 0.00728 -0.0404 0.3848 1.0000 8.000 1.2133 0.01392 0.00774 -0.0397 0.3702 1.0000 8.500 1.2628 0.01438 0.00831 -0.0389 0.3547 1.0000 9.000 1.3106 0.01490 0.00890 -0.0379 0.3375 1.0000 9.500 1.3561 0.01554 0.00960 -0.0367 0.3179 1.0000 10.000 1.3985 0.01630 0.01047 -0.0351 0.2960 1.0000 10.500 1.4367 0.01725 0.01154 -0.0331 0.2714 1.0000 11.000 1.4667 0.01853 0.01288 -0.0303 0.2434 1.0000 11.500 1.4786 0.02032 0.01466 -0.0252 0.2165 1.0000 12.000 1.4700 0.02307 0.01743 -0.0191 0.1938 1.0000 12.500 1.4622 0.02713 0.02154 -0.0160 0.1703 1.0000 13.000 1.4489 0.03250 0.02694 -0.0144 0.1484 1.0000 13.500 1.4317 0.03874 0.03318 -0.0136 0.1298 1.0000 14.000 1.4129 0.04553 0.03999 -0.0134 0.1139 1.0000 14.500 1.3943 0.05270 0.04721 -0.0138 0.1000 1.0000 15.000 1.3794 0.06014 0.05470 -0.0150 0.0875 1.0000 15.500 1.3660 0.06787 0.06251 -0.0166 0.0764 1.0000 16.000 1.3530 0.07599 0.07072 -0.0188 0.0667 1.0000 16.500 1.3405 0.08443 0.07925 -0.0213 0.0585 1.0000 17.000 1.3289 0.09311 0.08803 -0.0243 0.0513 1.0000 17.500 1.3187 0.10189 0.09691 -0.0276 0.0453 1.0000 18.000 1.3103 0.11061 0.10572 -0.0311 0.0401 1.0000 18.500 1.3023 0.11952 0.11473 -0.0351 0.0354 1.0000 19.000 1.2963 0.12817 0.12346 -0.0392 0.0315 1.0000 19.500 1.2911 0.13707 0.13255 -0.0437 0.0280 1.0000 20.000 1.2872 0.14567 0.14130 -0.0483 0.0247 1.0000 20.500 1.2827 0.15447 0.15023 -0.0534 0.0219 1.0000 21.000 1.2776 0.16353 0.15938 -0.0589 0.0193 1.0000 21.500 1.2722 0.17287 0.16890 -0.0648 0.0171 1.0000 22.000 1.2662 0.18238 0.17860 -0.0710 0.0151 1.0000 22.500 1.2626 0.19126 0.18755 -0.0771 0.0133 1.0000 23.000 1.2559 0.20120 0.19772 -0.0838 0.0119 1.0000 23.500 1.2529 0.21007 0.20667 -0.0901 0.0106 1.0000 24.000 1.2431 0.22120 0.21805 -0.0977 0.0096 1.0000 24.500 1.2437 0.22921 0.22607 -0.1037 0.0085 1.0000 25.000 1.2219 0.24478 0.24196 -0.1139 0.0081 1.0000 26.000 1.1414 0.31351 0.31058 -0.1423 0.0147 1.0000 26.500 1.1543 0.31857 0.31566 -0.1461 0.0139 1.0000 27.000 1.1689 0.32329 0.32042 -0.1490 0.0135 1.0000 27.500 1.1759 0.33288 0.32996 -0.1556 0.0124 1.0000 28.000 1.1875 0.33829 0.33539 -0.1598 0.0115 1.0000 28.500 1.1998 0.34235 0.33949 -0.1633 0.0111 1.0000 29.000 1.2100 0.34889 0.34601 -0.1680 0.0108 1.0000 29.500 1.2203 0.35600 0.35312 -0.1731 0.0098 1.0000 30.000 1.2310 0.36096 0.35810 -0.1774 0.0092 1.0000 30.500 1.2411 0.36508 0.36225 -0.1813 0.0088 1.0000 31.000 1.2521 0.36950 0.36670 -0.1848 0.0086 1.0000 31.500 1.2608 0.37663 0.37381 -0.1906 0.0082 1.0000 32.000 1.2703 0.38181 0.37901 -0.1950 0.0076 1.0000 32.500 1.2795 0.38628 0.38350 -0.1994 0.0070 1.0000 33.000 1.2880 0.38987 0.38713 -0.2035 0.0067 1.0000 33.500 1.2960 0.39452 0.39179 -0.2079 0.0065 1.0000 34.000 1.3053 0.40052 0.39779 -0.2127 0.0058 1.0000 34.500 1.3131 0.40480 0.40209 -0.2172 0.0054 1.0000 35.000 1.3200 0.40832 0.40565 -0.2215 0.0049 1.0000 35.500 1.3264 0.41137 0.40874 -0.2256 0.0048 1.0000 36.000 1.3333 0.41605 0.41342 -0.2302 0.0047 1.0000 36.500 1.3410 0.42144 0.41882 -0.2350 0.0044 1.0000 37.000 1.3474 0.42557 0.42297 -0.2394 0.0040 1.0000 37.500 1.3530 0.42925 0.42667 -0.2439 0.0037 1.0000 38.000 1.3581 0.43254 0.43000 -0.2484 0.0035 1.0000 38.500 1.3622 0.43524 0.43273 -0.2529 0.0033 1.0000 39.000 1.3657 0.43737 0.43489 -0.2572 0.0032 1.0000 40.000 1.3736 0.44336 0.44092 -0.2663 0.0031 1.0000