XFOIL Version 6.96 Calculated polar for: S5010 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -1.0344 0.03389 0.03145 -0.0113 1.0000 0.0034 -11.000 -1.0319 0.02937 0.02647 -0.0107 0.9339 0.0035 -10.750 -1.0227 0.02741 0.02415 -0.0087 0.8808 0.0036 -10.250 -0.9878 0.02442 0.02069 -0.0068 0.8378 0.0038 -10.000 -0.9672 0.02328 0.01936 -0.0061 0.8220 0.0039 -9.750 -0.9457 0.02223 0.01814 -0.0055 0.8078 0.0041 -9.500 -0.9236 0.02120 0.01692 -0.0049 0.7951 0.0042 -9.250 -0.9010 0.02022 0.01576 -0.0043 0.7832 0.0044 -9.000 -0.8781 0.01919 0.01453 -0.0037 0.7719 0.0045 -8.750 -0.8549 0.01819 0.01333 -0.0031 0.7617 0.0047 -8.500 -0.8309 0.01733 0.01229 -0.0026 0.7520 0.0048 -8.250 -0.8065 0.01652 0.01131 -0.0021 0.7425 0.0050 -8.000 -0.7814 0.01583 0.01049 -0.0017 0.7337 0.0051 -7.750 -0.7561 0.01521 0.00973 -0.0013 0.7251 0.0052 -7.500 -0.7314 0.01436 0.00872 -0.0008 0.7167 0.0056 -7.250 -0.7053 0.01390 0.00818 -0.0004 0.7088 0.0059 -7.000 -0.6786 0.01354 0.00776 -0.0002 0.7005 0.0062 -6.750 -0.6520 0.01319 0.00734 0.0001 0.6929 0.0065 -6.500 -0.6252 0.01284 0.00691 0.0004 0.6850 0.0069 -6.250 -0.5985 0.01246 0.00645 0.0006 0.6777 0.0073 -6.000 -0.5716 0.01212 0.00602 0.0009 0.6700 0.0077 -5.750 -0.5447 0.01174 0.00557 0.0012 0.6627 0.0081 -5.500 -0.5173 0.01152 0.00532 0.0013 0.6549 0.0088 -5.250 -0.4896 0.01136 0.00514 0.0015 0.6476 0.0094 -4.750 -0.4347 0.01090 0.00457 0.0018 0.6325 0.0107 -4.250 -0.3794 0.01049 0.00404 0.0022 0.6171 0.0115 -4.000 -0.3525 0.01006 0.00354 0.0024 0.6095 0.0124 -3.750 -0.3248 0.00987 0.00333 0.0026 0.6016 0.0133 -3.500 -0.2970 0.00970 0.00311 0.0027 0.5941 0.0142 -3.250 -0.2692 0.00950 0.00286 0.0028 0.5862 0.0149 -3.000 -0.2413 0.00934 0.00265 0.0030 0.5785 0.0156 -2.750 -0.2133 0.00920 0.00247 0.0031 0.5704 0.0160 -2.500 -0.1854 0.00900 0.00222 0.0032 0.5627 0.0165 -2.250 -0.1576 0.00880 0.00195 0.0033 0.5545 0.0174 -2.000 -0.1296 0.00864 0.00176 0.0034 0.5465 0.0185 -1.500 -0.0733 0.00842 0.00146 0.0036 0.5293 0.0214 -1.250 -0.0450 0.00835 0.00135 0.0037 0.5206 0.0234 -1.000 -0.0169 0.00823 0.00125 0.0037 0.5115 0.0333 -0.750 0.0108 0.00802 0.00114 0.0038 0.5028 0.0728 -0.500 0.0383 0.00779 0.00106 0.0039 0.4936 0.1276 -0.250 0.0656 0.00752 0.00099 0.0039 0.4844 0.1995 0.000 0.0924 0.00716 0.00093 0.0040 0.4754 0.3066 0.250 0.1191 0.00685 0.00089 0.0042 0.4657 0.4091 0.500 0.1454 0.00650 0.00087 0.0044 0.4559 0.5218 0.750 0.1705 0.00609 0.00087 0.0049 0.4462 0.6578 1.000 0.1911 0.00551 0.00089 0.0066 0.4367 0.8406 1.250 0.2251 0.00536 0.00100 0.0057 0.4251 0.9514 1.750 0.2950 0.00555 0.00107 0.0029 0.4021 0.9790 2.000 0.3280 0.00566 0.00111 0.0018 0.3901 0.9846 2.250 0.3631 0.00577 0.00115 0.0003 0.3771 0.9884 2.500 0.3969 0.00589 0.00120 -0.0010 0.3639 0.9924 2.750 0.4315 0.00601 0.00125 -0.0024 0.3497 0.9953 3.000 0.4668 0.00614 0.00131 -0.0041 0.3341 0.9978 3.250 0.5022 0.00627 0.00138 -0.0058 0.3192 1.0000 3.500 0.5285 0.00642 0.00146 -0.0055 0.3053 1.0000 3.750 0.5549 0.00657 0.00155 -0.0052 0.2918 1.0000 4.000 0.5813 0.00674 0.00167 -0.0050 0.2781 1.0000 4.250 0.6076 0.00691 0.00178 -0.0047 0.2640 1.0000 4.500 0.6339 0.00709 0.00191 -0.0044 0.2517 1.0000 5.000 0.6864 0.00747 0.00220 -0.0039 0.2252 1.0000 5.250 0.7126 0.00768 0.00236 -0.0037 0.2121 1.0000 5.500 0.7388 0.00790 0.00252 -0.0035 0.1996 1.0000 5.750 0.7649 0.00811 0.00271 -0.0032 0.1880 1.0000 6.000 0.7908 0.00836 0.00291 -0.0030 0.1748 1.0000 6.250 0.8167 0.00862 0.00312 -0.0027 0.1623 1.0000 6.500 0.8426 0.00889 0.00334 -0.0025 0.1506 1.0000 6.750 0.8683 0.00916 0.00359 -0.0023 0.1405 1.0000 7.000 0.8940 0.00943 0.00383 -0.0020 0.1300 1.0000 7.250 0.9195 0.00973 0.00410 -0.0018 0.1191 1.0000 7.500 0.9449 0.01004 0.00438 -0.0015 0.1091 1.0000 7.750 0.9701 0.01038 0.00468 -0.0013 0.0993 1.0000 8.000 0.9951 0.01075 0.00502 -0.0010 0.0890 1.0000 8.250 1.0198 0.01115 0.00537 -0.0007 0.0782 1.0000 8.500 1.0443 0.01156 0.00575 -0.0005 0.0677 1.0000 8.750 1.0687 0.01199 0.00614 -0.0002 0.0583 1.0000 9.000 1.0928 0.01244 0.00656 0.0001 0.0502 1.0000 9.250 1.1164 0.01296 0.00705 0.0004 0.0415 1.0000 9.500 1.1398 0.01347 0.00753 0.0007 0.0346 1.0000 9.750 1.1634 0.01394 0.00800 0.0010 0.0298 1.0000 10.000 1.1860 0.01451 0.00855 0.0014 0.0243 1.0000 10.250 1.2084 0.01506 0.00910 0.0018 0.0201 1.0000 10.500 1.2302 0.01566 0.00972 0.0023 0.0159 1.0000 10.750 1.2505 0.01638 0.01043 0.0028 0.0113 1.0000 11.000 1.2693 0.01722 0.01126 0.0035 0.0070 1.0000 11.250 1.2876 0.01804 0.01210 0.0042 0.0045 1.0000 11.500 1.3058 0.01880 0.01290 0.0049 0.0036 1.0000 11.750 1.3226 0.01961 0.01377 0.0058 0.0030 1.0000 12.000 1.3388 0.02039 0.01463 0.0067 0.0028 1.0000 12.250 1.3533 0.02122 0.01554 0.0077 0.0026 1.0000 12.500 1.3634 0.02212 0.01652 0.0093 0.0025 1.0000 12.750 1.3674 0.02326 0.01773 0.0111 0.0024 1.0000 13.000 1.3719 0.02470 0.01925 0.0122 0.0023 1.0000 13.250 1.3775 0.02626 0.02090 0.0129 0.0022 1.0000 13.500 1.3827 0.02800 0.02272 0.0133 0.0021 1.0000 13.750 1.3856 0.03009 0.02490 0.0135 0.0020 1.0000 14.000 1.3880 0.03233 0.02723 0.0135 0.0019 1.0000 14.250 1.3864 0.03510 0.03011 0.0132 0.0018 1.0000 14.500 1.3882 0.03758 0.03269 0.0129 0.0018 1.0000 14.750 1.3814 0.04117 0.03640 0.0121 0.0017 1.0000 15.000 1.3786 0.04438 0.03971 0.0112 0.0017 1.0000 15.250 1.3748 0.04779 0.04323 0.0102 0.0016 1.0000 15.500 1.3682 0.05169 0.04725 0.0089 0.0016 1.0000 15.750 1.3577 0.05622 0.05190 0.0073 0.0017 1.0000 16.000 1.3502 0.06053 0.05631 0.0056 0.0016 1.0000 16.250 1.3466 0.06444 0.06031 0.0040 0.0016 1.0000 16.500 1.3320 0.07014 0.06614 0.0015 0.0016 1.0000 16.750 1.3201 0.07564 0.07175 -0.0010 0.0016 1.0000 17.000 1.3039 0.08198 0.07822 -0.0040 0.0016 1.0000 17.250 1.2917 0.08784 0.08419 -0.0068 0.0015 1.0000 17.500 1.2684 0.09585 0.09234 -0.0108 0.0016 1.0000 17.750 1.2558 0.10209 0.09868 -0.0138 0.0016 1.0000 18.000 1.2378 0.10956 0.10628 -0.0177 0.0016 1.0000 18.250 1.2153 0.11809 0.11493 -0.0221 0.0016 1.0000