XFOIL Version 6.96 Calculated polar for: S1010 HPV airfoil 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 ------ -------- --------- --------- -------- -------- -------- -13.750 -0.9092 0.10699 0.10526 0.0181 1.0000 0.0025 -13.500 -1.0247 0.07966 0.07783 0.0013 1.0000 0.0021 -13.250 -1.1632 0.04517 0.04300 -0.0243 1.0000 0.0017 -13.000 -1.1967 0.03985 0.03746 -0.0231 1.0000 0.0018 -12.750 -1.2085 0.03627 0.03365 -0.0212 1.0000 0.0018 -12.500 -1.2096 0.03320 0.03034 -0.0198 1.0000 0.0018 -12.250 -1.2058 0.03044 0.02733 -0.0184 1.0000 0.0019 -12.000 -1.1963 0.02823 0.02490 -0.0173 1.0000 0.0019 -11.750 -1.1828 0.02646 0.02294 -0.0163 1.0000 0.0020 -11.500 -1.1668 0.02495 0.02127 -0.0153 1.0000 0.0021 -11.250 -1.1494 0.02357 0.01972 -0.0145 1.0000 0.0022 -11.000 -1.1301 0.02244 0.01846 -0.0138 1.0000 0.0023 -10.750 -1.1106 0.02128 0.01714 -0.0130 1.0000 0.0024 -10.500 -1.0907 0.02011 0.01579 -0.0122 1.0000 0.0024 -10.250 -1.0694 0.01916 0.01470 -0.0116 1.0000 0.0025 -10.000 -1.0477 0.01822 0.01362 -0.0109 1.0000 0.0026 -9.750 -1.0253 0.01739 0.01267 -0.0103 1.0000 0.0028 -9.500 -1.0026 0.01657 0.01172 -0.0097 1.0000 0.0029 -9.250 -0.9795 0.01583 0.01086 -0.0091 1.0000 0.0030 -9.000 -0.9560 0.01513 0.01005 -0.0085 1.0000 0.0031 -8.750 -0.9319 0.01453 0.00936 -0.0080 1.0000 0.0032 -8.500 -0.9076 0.01398 0.00872 -0.0075 1.0000 0.0033 -8.250 -0.8841 0.01317 0.00776 -0.0068 1.0000 0.0040 -8.000 -0.8597 0.01262 0.00718 -0.0063 1.0000 0.0048 -7.750 -0.8348 0.01219 0.00672 -0.0058 1.0000 0.0057 -7.500 -0.8097 0.01180 0.00628 -0.0054 1.0000 0.0063 -7.250 -0.7849 0.01135 0.00578 -0.0049 1.0000 0.0077 -7.000 -0.7598 0.01098 0.00541 -0.0044 1.0000 0.0092 -6.750 -0.7345 0.01069 0.00508 -0.0039 1.0000 0.0104 -6.500 -0.7092 0.01042 0.00476 -0.0034 1.0000 0.0111 -6.250 -0.6840 0.01016 0.00446 -0.0029 1.0000 0.0116 -6.000 -0.6593 0.00979 0.00405 -0.0022 1.0000 0.0132 -5.750 -0.6347 0.00948 0.00374 -0.0016 1.0000 0.0150 -5.500 -0.6101 0.00921 0.00346 -0.0009 1.0000 0.0164 -5.250 -0.5855 0.00898 0.00320 -0.0002 1.0000 0.0175 -5.000 -0.5612 0.00868 0.00292 0.0005 1.0000 0.0219 -4.750 -0.5371 0.00842 0.00266 0.0013 1.0000 0.0281 -4.500 -0.5131 0.00817 0.00245 0.0021 1.0000 0.0361 -4.250 -0.4825 0.00794 0.00226 0.0015 0.9982 0.0434 -4.000 -0.4509 0.00777 0.00209 0.0006 0.9961 0.0490 -3.750 -0.4190 0.00757 0.00193 -0.0003 0.9941 0.0576 -3.500 -0.3885 0.00739 0.00179 -0.0009 0.9914 0.0653 -3.000 -0.3259 0.00705 0.00152 -0.0024 0.9859 0.0866 -2.750 -0.2938 0.00688 0.00142 -0.0034 0.9832 0.1008 -2.500 -0.2613 0.00669 0.00131 -0.0044 0.9743 0.1189 -2.250 -0.2269 0.00654 0.00117 -0.0056 0.9481 0.1328 -2.000 -0.2016 0.00649 0.00106 -0.0047 0.9072 0.1454 -1.750 -0.1766 0.00644 0.00097 -0.0038 0.8773 0.1610 -1.500 -0.1510 0.00636 0.00089 -0.0032 0.8503 0.1849 -1.250 -0.1249 0.00628 0.00081 -0.0027 0.8248 0.2103 -1.000 -0.0989 0.00618 0.00075 -0.0023 0.7964 0.2457 -0.750 -0.0734 0.00614 0.00069 -0.0017 0.7498 0.2832 -0.500 -0.0493 0.00624 0.00064 -0.0010 0.6531 0.3351 -0.250 -0.0250 0.00640 0.00063 -0.0004 0.5456 0.3925 0.000 0.0000 0.00641 0.00063 0.0000 0.4678 0.4680 0.250 0.0249 0.00641 0.00063 0.0004 0.3909 0.5460 0.500 0.0493 0.00624 0.00064 0.0009 0.3348 0.6523 0.750 0.0734 0.00614 0.00069 0.0017 0.2826 0.7499 1.000 0.0990 0.00618 0.00075 0.0023 0.2459 0.7965 1.250 0.1249 0.00628 0.00081 0.0027 0.2104 0.8247 1.500 0.1510 0.00636 0.00089 0.0032 0.1847 0.8500 1.750 0.1766 0.00644 0.00097 0.0038 0.1613 0.8771 2.000 0.2017 0.00649 0.00106 0.0047 0.1454 0.9072 2.250 0.2270 0.00654 0.00117 0.0056 0.1328 0.9481 2.500 0.2614 0.00669 0.00131 0.0043 0.1189 0.9744 2.750 0.2940 0.00687 0.00142 0.0033 0.1024 0.9833 3.000 0.3261 0.00705 0.00152 0.0024 0.0864 0.9859 3.500 0.3887 0.00739 0.00179 0.0008 0.0655 0.9916 3.750 0.4193 0.00757 0.00193 0.0002 0.0574 0.9942 4.000 0.4512 0.00777 0.00209 -0.0007 0.0490 0.9962 4.250 0.4828 0.00795 0.00226 -0.0015 0.0433 0.9984 4.500 0.5127 0.00817 0.00245 -0.0020 0.0362 1.0000 4.750 0.5366 0.00842 0.00266 -0.0012 0.0282 1.0000 5.000 0.5608 0.00868 0.00292 -0.0005 0.0220 1.0000 5.250 0.5851 0.00898 0.00320 0.0003 0.0176 1.0000 5.500 0.6098 0.00921 0.00346 0.0010 0.0165 1.0000 5.750 0.6344 0.00948 0.00374 0.0017 0.0150 1.0000 6.000 0.6591 0.00979 0.00405 0.0023 0.0132 1.0000 6.250 0.6838 0.01016 0.00446 0.0029 0.0115 1.0000 6.500 0.7091 0.01043 0.00476 0.0034 0.0111 1.0000 6.750 0.7345 0.01069 0.00508 0.0039 0.0104 1.0000 7.000 0.7599 0.01098 0.00541 0.0044 0.0092 1.0000 7.250 0.7850 0.01135 0.00579 0.0048 0.0078 1.0000 7.500 0.8099 0.01180 0.00627 0.0054 0.0063 1.0000 7.750 0.8350 0.01219 0.00672 0.0058 0.0057 1.0000 8.000 0.8598 0.01263 0.00719 0.0063 0.0048 1.0000 8.250 0.8843 0.01317 0.00776 0.0068 0.0040 1.0000 8.500 0.9079 0.01397 0.00871 0.0074 0.0033 1.0000 8.750 0.9322 0.01453 0.00935 0.0079 0.0032 1.0000 9.000 0.9562 0.01514 0.01006 0.0085 0.0031 1.0000 9.250 0.9798 0.01582 0.01086 0.0090 0.0030 1.0000 9.500 1.0031 0.01654 0.01168 0.0096 0.0029 1.0000 9.750 1.0259 0.01734 0.01261 0.0102 0.0027 1.0000 10.000 1.0481 0.01822 0.01362 0.0108 0.0026 1.0000 10.250 1.0699 0.01914 0.01467 0.0115 0.0025 1.0000 10.500 1.0909 0.02017 0.01585 0.0122 0.0024 1.0000 10.750 1.1116 0.02117 0.01702 0.0128 0.0023 1.0000 11.000 1.1312 0.02234 0.01834 0.0136 0.0023 1.0000 11.250 1.1497 0.02362 0.01978 0.0144 0.0022 1.0000 11.500 1.1677 0.02491 0.02122 0.0152 0.0021 1.0000 11.750 1.1841 0.02637 0.02283 0.0161 0.0020 1.0000 12.000 1.1967 0.02829 0.02497 0.0171 0.0019 1.0000 12.250 1.2062 0.03050 0.02739 0.0183 0.0019 1.0000 12.500 1.2112 0.03311 0.03024 0.0196 0.0019 1.0000 12.750 1.2095 0.03628 0.03366 0.0210 0.0018 1.0000 13.000 1.1886 0.04075 0.03840 0.0232 0.0017 1.0000 13.250 1.1499 0.04722 0.04512 0.0231 0.0017 1.0000 13.500 1.0185 0.08114 0.07931 -0.0025 0.0021 1.0000 13.750 0.9106 0.10708 0.10534 -0.0183 0.0025 1.0000