XFOIL Version 6.94 Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 1.000 0.4830 0.01061 0.00299 -0.0586 0.5438 0.0442 1.500 0.5355 0.01028 0.00261 -0.0577 0.5248 0.0461 3.500 0.7701 0.00838 0.00248 -0.0604 0.4050 1.0000 4.000 0.8170 0.00897 0.00276 -0.0587 0.3396 1.0000 4.500 0.8553 0.01047 0.00344 -0.0560 0.2089 1.0000 5.000 0.8890 0.01255 0.00462 -0.0528 0.0464 1.0000 5.500 0.9331 0.01353 0.00547 -0.0509 0.0281 1.0000 6.000 0.9804 0.01414 0.00611 -0.0494 0.0253 1.0000 6.500 1.0274 0.01474 0.00668 -0.0480 0.0198 1.0000 7.000 1.0738 0.01537 0.00735 -0.0465 0.0172 1.0000 7.500 1.1164 0.01631 0.00822 -0.0446 0.0031 1.0000 8.000 1.1587 0.01722 0.00924 -0.0425 0.0028 1.0000 8.500 1.1983 0.01825 0.01041 -0.0401 0.0028 1.0000 9.000 1.2341 0.01946 0.01180 -0.0371 0.0029 1.0000 9.500 1.2655 0.02080 0.01330 -0.0336 0.0030 1.0000 10.000 1.2896 0.02220 0.01487 -0.0290 0.0032 1.0000 10.500 1.3065 0.02375 0.01660 -0.0235 0.0034 1.0000 11.000 1.3197 0.02575 0.01879 -0.0187 0.0035 1.0000 11.500 1.3289 0.02844 0.02171 -0.0147 0.0038 1.0000 12.000 1.3325 0.03220 0.02571 -0.0121 0.0039 1.0000 12.500 1.3339 0.03683 0.03058 -0.0107 0.0041 1.0000 13.000 1.3380 0.04164 0.03561 -0.0103 0.0043 1.0000 13.500 1.3367 0.04750 0.04171 -0.0107 0.0046 1.0000 14.000 1.3268 0.05482 0.04928 -0.0120 0.0048 1.0000 14.500 1.3114 0.06322 0.05791 -0.0140 0.0050 1.0000 15.000 1.2938 0.07247 0.06740 -0.0168 0.0052 1.0000 15.500 1.2758 0.08228 0.07743 -0.0201 0.0054 1.0000 16.000 1.2595 0.09220 0.08753 -0.0237 0.0055 1.0000 16.500 1.2556 0.10084 0.09639 -0.0272 0.0058 1.0000 17.000 1.2478 0.11029 0.10614 -0.0310 0.0062 1.0000 17.500 1.2352 0.12076 0.11690 -0.0355 0.0065 1.0000 18.000 1.2179 0.13269 0.12914 -0.0413 0.0069 1.0000 18.500 1.1977 0.14576 0.14249 -0.0483 0.0071 1.0000 19.000 1.1759 0.16030 0.15731 -0.0572 0.0071 1.0000 19.500 1.1485 0.17706 0.17435 -0.0675 0.0072 1.0000 20.000 1.1153 0.19769 0.19525 -0.0801 0.0067 1.0000