XFOIL Version 6.94 Calculated polar for: GOE 117 (MVA MK.4) 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 0.4693 0.00965 0.00242 -0.1056 0.6546 0.3888 1.000 0.5991 0.00864 0.00267 -0.1099 0.6278 1.0000 1.500 0.6507 0.00900 0.00286 -0.1093 0.6164 1.0000 2.000 0.7018 0.00927 0.00308 -0.1085 0.6047 1.0000 2.500 0.7425 0.00946 0.00291 -0.1050 0.5506 1.0000 3.000 0.7849 0.00968 0.00306 -0.1021 0.4874 1.0000 3.500 0.8240 0.01044 0.00335 -0.0989 0.3740 1.0000 4.000 0.8344 0.01388 0.00516 -0.0917 0.0312 1.0000 4.500 0.8787 0.01464 0.00590 -0.0895 0.0094 1.0000 5.000 0.9217 0.01547 0.00693 -0.0869 0.0096 1.0000 5.500 0.9585 0.01669 0.00840 -0.0831 0.0108 1.0000 6.000 0.9810 0.01861 0.01056 -0.0769 0.0123 1.0000 6.500 0.9795 0.02142 0.01351 -0.0669 0.0140 1.0000 8.500 1.2215 0.05311 0.04698 -0.0631 0.0360 1.0000 9.000 1.2186 0.05711 0.05172 -0.0550 0.0314 1.0000 9.500 1.2283 0.06505 0.05990 -0.0512 0.0276 1.0000 10.000 1.1907 0.06707 0.06268 -0.0393 0.0253 1.0000 10.500 1.0852 0.07020 0.06643 -0.0296 0.0271 1.0000 11.000 1.0398 0.07910 0.07565 -0.0274 0.0271 1.0000 11.500 0.9980 0.08997 0.08678 -0.0288 0.0274 1.0000 12.000 0.9601 0.10165 0.09866 -0.0326 0.0275 1.0000 12.500 0.9241 0.11323 0.11044 -0.0384 0.0276 1.0000 13.000 0.8884 0.12436 0.12176 -0.0458 0.0277 1.0000 13.500 0.8599 0.13657 0.13411 -0.0543 0.0277 1.0000 14.000 0.9221 0.15759 0.15476 -0.0646 0.0263 1.0000 14.500 0.9264 0.16727 0.16443 -0.0691 0.0245 1.0000 15.000 0.9291 0.17824 0.17536 -0.0745 0.0236 1.0000 15.500 0.9322 0.18954 0.18662 -0.0811 0.0219 1.0000 16.000 0.9459 0.19629 0.19337 -0.0830 0.0203 1.0000 16.500 0.9492 0.20759 0.20462 -0.0904 0.0190 1.0000 17.000 0.8189 0.21617 0.21385 -0.1042 0.0201 1.0000 17.500 0.8237 0.22521 0.22291 -0.1091 0.0184 1.0000 18.000 0.8340 0.23325 0.23096 -0.1120 0.0170 1.0000 18.500 0.8386 0.24262 0.24034 -0.1172 0.0157 1.0000 19.000 0.8484 0.25049 0.24823 -0.1203 0.0144 1.0000 19.500 0.8550 0.25990 0.25765 -0.1246 0.0138 1.0000 20.000 0.8629 0.26884 0.26661 -0.1286 0.0124 1.0000 20.500 0.8739 0.27699 0.27478 -0.1310 0.0114 1.0000 21.000 0.8792 0.28674 0.28454 -0.1359 0.0111 1.0000 21.500 0.8872 0.29594 0.29376 -0.1396 0.0103 1.0000 22.000 0.8954 0.30466 0.30250 -0.1430 0.0094 1.0000 22.500 0.9038 0.31370 0.31157 -0.1459 0.0090 1.0000 23.000 0.9104 0.32345 0.32134 -0.1501 0.0088 1.0000 23.500 0.9178 0.33308 0.33099 -0.1537 0.0082 1.0000 24.000 0.9251 0.34252 0.34046 -0.1571 0.0077 1.0000 24.500 0.9319 0.35194 0.34990 -0.1605 0.0073 1.0000 25.500 0.9448 0.37089 0.36890 -0.1667 0.0068 1.0000 26.000 0.9506 0.38077 0.37881 -0.1703 0.0067 1.0000 26.500 0.9565 0.39062 0.38869 -0.1738 0.0066 1.0000 27.000 0.9622 0.40072 0.39881 -0.1771 0.0064 1.0000 27.500 0.9675 0.41062 0.40875 -0.1803 0.0061 1.0000 28.000 0.9724 0.42045 0.41861 -0.1835 0.0060 1.0000 28.500 0.9769 0.43030 0.42849 -0.1867 0.0058 1.0000 29.000 0.9810 0.44018 0.43840 -0.1898 0.0056 1.0000 29.500 0.9850 0.45012 0.44837 -0.1930 0.0054 1.0000 30.000 0.9884 0.45988 0.45817 -0.1961 0.0054 1.0000 30.500 0.9914 0.46968 0.46800 -0.1991 0.0052 1.0000 31.000 0.9941 0.47943 0.47779 -0.2022 0.0051 1.0000 31.500 0.9965 0.48920 0.48759 -0.2052 0.0051 1.0000 32.000 0.9986 0.49893 0.49736 -0.2082 0.0051 1.0000 32.500 1.0003 0.50873 0.50719 -0.2111 0.0051 1.0000 33.000 1.0015 0.51825 0.51674 -0.2140 0.0051 1.0000 33.500 1.0026 0.52777 0.52630 -0.2169 0.0052 1.0000 34.000 1.0031 0.53742 0.53599 -0.2198 0.0050 1.0000 34.500 1.0035 0.54680 0.54540 -0.2226 0.0051 1.0000 35.000 1.0034 0.55611 0.55475 -0.2254 0.0051 1.0000 35.500 1.0032 0.56547 0.56414 -0.2282 0.0052 1.0000 36.000 1.0024 0.57459 0.57331 -0.2309 0.0052 1.0000 36.500 1.0015 0.58375 0.58250 -0.2337 0.0052 1.0000 37.000 0.9999 0.59255 0.59134 -0.2363 0.0053 1.0000 37.500 0.9981 0.60132 0.60014 -0.2389 0.0053 1.0000 38.000 0.9961 0.61005 0.60891 -0.2415 0.0052 1.0000 38.500 0.9935 0.61847 0.61737 -0.2441 0.0051 1.0000 39.000 0.9904 0.62682 0.62576 -0.2466 0.0050 1.0000 41.000 0.9768 0.66185 0.66090 -0.2561 0.0048 1.0000 41.500 0.9731 0.67002 0.66910 -0.2583 0.0047 1.0000 42.000 0.9692 0.67832 0.67743 -0.2605 0.0046 1.0000 42.500 0.9648 0.68622 0.68535 -0.2626 0.0044 1.0000 43.000 0.9599 0.69379 0.69296 -0.2647 0.0042 1.0000 43.500 0.9546 0.70105 0.70025 -0.2668 0.0040 1.0000 44.000 0.9490 0.70781 0.70705 -0.2688 0.0037 1.0000 44.500 0.9430 0.71438 0.71364 -0.2708 0.0035 1.0000 45.000 0.9366 0.72041 0.71970 -0.2728 0.0032 1.0000 45.500 0.9295 0.72601 0.72533 -0.2748 0.0031 1.0000 47.000 0.9095 0.74491 0.74430 -0.2800 0.0030 1.0000 47.500 0.9026 0.75045 0.74987 -0.2817 0.0030 1.0000 48.000 0.8954 0.75549 0.75494 -0.2832 0.0030 1.0000 48.500 0.8880 0.76022 0.75969 -0.2847 0.0029 1.0000 49.000 0.8801 0.76442 0.76391 -0.2862 0.0028 1.0000 49.500 0.8721 0.76835 0.76787 -0.2877 0.0027 1.0000 50.000 0.8637 0.77169 0.77124 -0.2891 0.0025 1.0000 50.500 0.8550 0.77464 0.77421 -0.2905 0.0023 1.0000 51.000 0.8461 0.77706 0.77666 -0.2919 0.0021 1.0000 51.500 0.8370 0.77920 0.77882 -0.2932 0.0019 1.0000 52.000 0.8275 0.78047 0.78011 -0.2944 0.0018 1.0000 52.500 0.8176 0.78118 0.78085 -0.2956 0.0016 1.0000 53.000 0.8076 0.78172 0.78141 -0.2969 0.0015 1.0000 53.500 0.7967 0.78163 0.78134 -0.2981 0.0015 1.0000 54.500 0.7780 0.78406 0.78380 -0.2999 0.0014 1.0000 55.000 0.7681 0.78375 0.78351 -0.3008 0.0014 1.0000 55.500 0.7578 0.78263 0.78241 -0.3015 0.0013 1.0000 56.000 0.7473 0.78108 0.78088 -0.3023 0.0013 1.0000 56.500 0.7365 0.77901 0.77884 -0.3031 0.0012 1.0000 57.000 0.7256 0.77665 0.77650 -0.3038 0.0010 1.0000 57.500 0.7145 0.77374 0.77360 -0.3046 0.0010 1.0000 58.000 0.7032 0.77015 0.77003 -0.3052 0.0009 1.0000 58.500 0.6917 0.76606 0.76596 -0.3058 0.0008 1.0000 59.500 0.6692 0.75883 0.75876 -0.3067 0.0007 1.0000 60.000 0.6577 0.75408 0.75402 -0.3071 0.0007 1.0000