XFOIL Version 6.96 Calculated polar for: EPPLER E836 HYDROFOIL AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.750 -0.8227 0.04715 0.04377 -0.0430 1.0000 0.0115 -10.500 -0.8441 0.04348 0.03986 -0.0393 1.0000 0.0112 -10.250 -0.8639 0.03988 0.03599 -0.0345 1.0000 0.0107 -10.000 -0.8884 0.03398 0.02947 -0.0281 1.0000 0.0097 -9.750 -0.8882 0.03035 0.02541 -0.0246 1.0000 0.0093 -9.500 -0.8791 0.02797 0.02277 -0.0223 1.0000 0.0093 -9.250 -0.8680 0.02676 0.02145 -0.0202 1.0000 0.0096 -9.000 -0.8598 0.02562 0.02020 -0.0174 1.0000 0.0098 -8.750 -0.8343 0.02427 0.01872 -0.0181 0.9933 0.0104 -8.500 -0.8029 0.02270 0.01698 -0.0197 0.9871 0.0110 -8.250 -0.7710 0.02068 0.01478 -0.0212 0.9819 0.0111 -8.000 -0.7404 0.01911 0.01306 -0.0224 0.9738 0.0115 -7.750 -0.7099 0.01791 0.01174 -0.0236 0.9651 0.0123 -7.500 -0.6804 0.01706 0.01078 -0.0245 0.9555 0.0129 -7.250 -0.6687 0.01528 0.00882 -0.0222 0.9411 0.0145 -7.000 -0.6514 0.01466 0.00812 -0.0206 0.9297 0.0158 -6.750 -0.6330 0.01414 0.00752 -0.0190 0.9201 0.0179 -6.500 -0.6163 0.01349 0.00676 -0.0171 0.9120 0.0220 -6.250 -0.5969 0.01300 0.00622 -0.0157 0.9043 0.0268 -6.000 -0.5782 0.01244 0.00563 -0.0141 0.8978 0.0366 -5.750 -0.5618 0.01167 0.00508 -0.0124 0.8908 0.0783 -5.500 -0.5454 0.01095 0.00463 -0.0107 0.8853 0.1427 -5.250 -0.5284 0.01021 0.00423 -0.0092 0.8790 0.2171 -5.000 -0.5112 0.00952 0.00386 -0.0076 0.8737 0.2974 -4.750 -0.4949 0.00878 0.00351 -0.0059 0.8686 0.3917 -4.500 -0.4790 0.00806 0.00320 -0.0040 0.8630 0.4934 -4.250 -0.4594 0.00765 0.00305 -0.0025 0.8587 0.5698 -4.000 -0.4361 0.00748 0.00300 -0.0016 0.8543 0.6200 -3.750 -0.4113 0.00740 0.00298 -0.0010 0.8498 0.6535 -3.500 -0.3850 0.00740 0.00293 -0.0007 0.8458 0.6734 -3.250 -0.3585 0.00742 0.00292 -0.0004 0.8422 0.6900 -3.000 -0.3316 0.00743 0.00291 -0.0002 0.8378 0.7035 -2.750 -0.3044 0.00745 0.00289 -0.0001 0.8337 0.7138 -2.500 -0.2769 0.00748 0.00289 0.0000 0.8303 0.7230 -2.250 -0.2497 0.00752 0.00289 0.0001 0.8263 0.7327 -2.000 -0.2221 0.00755 0.00290 0.0001 0.8221 0.7405 -1.750 -0.1944 0.00757 0.00288 0.0001 0.8183 0.7474 -1.500 -0.1666 0.00762 0.00290 0.0002 0.8150 0.7546 -1.250 -0.1391 0.00763 0.00291 0.0002 0.8105 0.7613 -1.000 -0.1113 0.00766 0.00294 0.0001 0.8063 0.7676 -0.750 -0.0836 0.00768 0.00292 0.0001 0.8027 0.7738 -0.500 -0.0556 0.00770 0.00296 0.0001 0.7987 0.7788 -0.250 -0.0280 0.00772 0.00298 0.0000 0.7939 0.7848 0.000 0.0000 0.00771 0.00296 0.0000 0.7896 0.7896 0.250 0.0279 0.00772 0.00298 0.0000 0.7848 0.7939 0.500 0.0555 0.00770 0.00296 -0.0001 0.7788 0.7987 0.750 0.0835 0.00768 0.00292 -0.0001 0.7738 0.8027 1.000 0.1112 0.00766 0.00294 -0.0001 0.7675 0.8063 1.250 0.1390 0.00763 0.00291 -0.0001 0.7614 0.8105 1.500 0.1666 0.00762 0.00290 -0.0002 0.7546 0.8150 1.750 0.1943 0.00756 0.00288 -0.0001 0.7474 0.8183 2.000 0.2220 0.00755 0.00290 -0.0001 0.7405 0.8220 2.250 0.2496 0.00752 0.00288 -0.0001 0.7326 0.8263 2.500 0.2768 0.00748 0.00289 0.0000 0.7230 0.8303 2.750 0.3042 0.00745 0.00289 0.0001 0.7138 0.8337 3.000 0.3315 0.00743 0.00291 0.0002 0.7034 0.8378 3.250 0.3584 0.00742 0.00293 0.0004 0.6901 0.8422 3.500 0.3849 0.00740 0.00293 0.0007 0.6734 0.8458 3.750 0.4112 0.00740 0.00298 0.0010 0.6539 0.8497 4.000 0.4360 0.00748 0.00300 0.0017 0.6203 0.8543 4.250 0.4592 0.00765 0.00305 0.0025 0.5699 0.8587 4.500 0.4787 0.00806 0.00320 0.0041 0.4924 0.8631 4.750 0.4950 0.00875 0.00350 0.0059 0.3949 0.8686 5.000 0.5110 0.00951 0.00386 0.0077 0.2984 0.8737 5.250 0.5282 0.01020 0.00423 0.0092 0.2186 0.8790 5.500 0.5452 0.01093 0.00462 0.0107 0.1441 0.8853 5.750 0.5612 0.01168 0.00508 0.0125 0.0777 0.8909 6.000 0.5777 0.01243 0.00563 0.0142 0.0366 0.8979 6.250 0.5964 0.01299 0.00621 0.0158 0.0267 0.9043 6.500 0.6156 0.01350 0.00677 0.0172 0.0218 0.9122 6.750 0.6313 0.01422 0.00761 0.0193 0.0184 0.9204 7.000 0.6508 0.01464 0.00810 0.0207 0.0157 0.9298 7.250 0.6679 0.01528 0.00883 0.0224 0.0145 0.9414 7.500 0.6798 0.01707 0.01078 0.0247 0.0128 0.9558 7.750 0.7098 0.01784 0.01167 0.0237 0.0121 0.9652 8.000 0.7400 0.01913 0.01309 0.0225 0.0116 0.9739 8.250 0.7707 0.02068 0.01478 0.0212 0.0112 0.9820 8.500 0.8026 0.02267 0.01695 0.0198 0.0110 0.9872 8.750 0.8337 0.02444 0.01891 0.0183 0.0105 0.9933 9.000 0.8604 0.02592 0.02053 0.0173 0.0099 1.0000 9.250 0.8672 0.02608 0.02069 0.0202 0.0094 1.0000 9.500 0.8785 0.02801 0.02281 0.0224 0.0093 1.0000 9.750 0.8881 0.02989 0.02488 0.0246 0.0091 1.0000 10.000 0.8950 0.03190 0.02709 0.0270 0.0090 1.0000 10.250 0.8922 0.03527 0.03086 0.0308 0.0093 1.0000 10.500 0.8425 0.04359 0.03999 0.0395 0.0111 1.0000