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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.250 -0.9927 0.04542 0.04355 -0.0209 1.0000 0.0048 -11.000 -1.0265 0.03903 0.03682 -0.0196 1.0000 0.0047 -10.750 -1.0229 0.03626 0.03385 -0.0188 1.0000 0.0048 -10.500 -1.0266 0.03199 0.02921 -0.0174 1.0000 0.0048 -10.250 -1.0187 0.02916 0.02609 -0.0162 1.0000 0.0049 -10.000 -1.0058 0.02694 0.02362 -0.0152 1.0000 0.0050 -9.750 -0.9917 0.02474 0.02115 -0.0141 1.0000 0.0051 -9.500 -0.9745 0.02299 0.01916 -0.0131 1.0000 0.0052 -9.250 -0.9552 0.02156 0.01752 -0.0122 1.0000 0.0053 -9.000 -0.9349 0.02025 0.01601 -0.0114 1.0000 0.0054 -8.750 -0.9214 0.01725 0.01258 -0.0098 1.0000 0.0056 -8.500 -0.9013 0.01577 0.01092 -0.0088 1.0000 0.0062 -8.250 -0.8773 0.01515 0.01024 -0.0083 1.0000 0.0066 -8.000 -0.8529 0.01462 0.00965 -0.0078 1.0000 0.0072 -7.750 -0.8286 0.01401 0.00895 -0.0072 1.0000 0.0078 -7.500 -0.8040 0.01347 0.00833 -0.0067 1.0000 0.0083 -7.250 -0.7818 0.01232 0.00700 -0.0057 1.0000 0.0094 -7.000 -0.7575 0.01174 0.00637 -0.0051 1.0000 0.0107 -6.750 -0.7324 0.01135 0.00594 -0.0046 1.0000 0.0120 -6.500 -0.7070 0.01107 0.00562 -0.0041 1.0000 0.0129 -6.250 -0.6836 0.01032 0.00477 -0.0032 1.0000 0.0151 -6.000 -0.6589 0.00994 0.00438 -0.0026 1.0000 0.0172 -5.750 -0.6340 0.00967 0.00407 -0.0020 1.0000 0.0190 -5.500 -0.6098 0.00927 0.00361 -0.0012 1.0000 0.0213 -5.250 -0.5858 0.00888 0.00325 -0.0004 1.0000 0.0266 -5.000 -0.5617 0.00852 0.00293 0.0004 1.0000 0.0353 -4.750 -0.5377 0.00824 0.00269 0.0012 1.0000 0.0459 -4.500 -0.5135 0.00803 0.00249 0.0020 1.0000 0.0537 -4.250 -0.4896 0.00782 0.00230 0.0028 1.0000 0.0618 -4.000 -0.4659 0.00761 0.00212 0.0037 1.0000 0.0706 -3.750 -0.4424 0.00744 0.00197 0.0046 1.0000 0.0795 -3.500 -0.4192 0.00727 0.00184 0.0056 1.0000 0.0900 -3.250 -0.3964 0.00711 0.00172 0.0066 1.0000 0.1030 -3.000 -0.3718 0.00695 0.00162 0.0072 0.9997 0.1176 -2.750 -0.3380 0.00676 0.00152 0.0058 0.9979 0.1377 -2.500 -0.3006 0.00658 0.00143 0.0037 0.9953 0.1599 -2.250 -0.2578 0.00633 0.00131 0.0005 0.9900 0.1913 -2.000 -0.2131 0.00605 0.00118 -0.0032 0.9840 0.2319 -1.750 -0.1797 0.00578 0.00109 -0.0044 0.9756 0.2808 -1.500 -0.1479 0.00541 0.00099 -0.0054 0.9668 0.3581 -1.250 -0.1197 0.00499 0.00090 -0.0055 0.9554 0.4576 -1.000 -0.0955 0.00444 0.00081 -0.0047 0.9413 0.5959 -0.750 -0.0735 0.00393 0.00078 -0.0033 0.9255 0.7414 -0.500 -0.0497 0.00376 0.00079 -0.0021 0.9080 0.8078 -0.250 -0.0248 0.00371 0.00079 -0.0010 0.8898 0.8424 0.000 0.0000 0.00369 0.00079 0.0000 0.8690 0.8690 0.250 0.0249 0.00371 0.00079 0.0010 0.8424 0.8898 0.500 0.0498 0.00376 0.00079 0.0021 0.8082 0.9084 0.750 0.0735 0.00393 0.00078 0.0033 0.7411 0.9256 1.000 0.0955 0.00444 0.00081 0.0047 0.5950 0.9413 1.250 0.1198 0.00499 0.00090 0.0055 0.4571 0.9553 1.500 0.1480 0.00540 0.00099 0.0053 0.3599 0.9668 1.750 0.1798 0.00578 0.00109 0.0044 0.2808 0.9757 2.000 0.2131 0.00605 0.00118 0.0032 0.2319 0.9840 2.250 0.2579 0.00633 0.00131 -0.0005 0.1913 0.9900 2.500 0.3008 0.00658 0.00143 -0.0038 0.1600 0.9953 2.750 0.3381 0.00676 0.00152 -0.0059 0.1378 0.9979 3.000 0.3719 0.00695 0.00162 -0.0073 0.1174 0.9997 3.250 0.3964 0.00711 0.00172 -0.0066 0.1033 1.0000 3.500 0.4192 0.00727 0.00184 -0.0056 0.0902 1.0000 3.750 0.4424 0.00744 0.00197 -0.0046 0.0795 1.0000 4.000 0.4659 0.00761 0.00212 -0.0037 0.0707 1.0000 4.250 0.4896 0.00782 0.00230 -0.0028 0.0618 1.0000 4.500 0.5135 0.00803 0.00249 -0.0020 0.0537 1.0000 4.750 0.5377 0.00824 0.00269 -0.0012 0.0460 1.0000 5.000 0.5618 0.00852 0.00293 -0.0004 0.0353 1.0000 5.250 0.5858 0.00888 0.00325 0.0004 0.0265 1.0000 5.500 0.6099 0.00927 0.00361 0.0012 0.0214 1.0000 5.750 0.6341 0.00967 0.00407 0.0020 0.0190 1.0000 6.000 0.6591 0.00994 0.00438 0.0026 0.0173 1.0000 6.250 0.6837 0.01032 0.00477 0.0032 0.0151 1.0000 6.500 0.7071 0.01107 0.00562 0.0041 0.0129 1.0000 6.750 0.7325 0.01136 0.00595 0.0046 0.0120 1.0000 7.000 0.7576 0.01173 0.00636 0.0051 0.0107 1.0000 7.250 0.7819 0.01232 0.00700 0.0057 0.0094 1.0000 7.500 0.8037 0.01355 0.00841 0.0067 0.0084 1.0000 7.750 0.8287 0.01399 0.00893 0.0072 0.0078 1.0000 8.000 0.8529 0.01464 0.00967 0.0078 0.0073 1.0000 8.250 0.8774 0.01516 0.01025 0.0083 0.0066 1.0000 8.500 0.9014 0.01575 0.01090 0.0088 0.0062 1.0000 8.750 0.9218 0.01717 0.01250 0.0097 0.0057 1.0000 9.000 0.9350 0.02025 0.01600 0.0114 0.0054 1.0000 9.250 0.9555 0.02151 0.01747 0.0122 0.0053 1.0000 9.500 0.9752 0.02286 0.01901 0.0130 0.0052 1.0000 9.750 0.9916 0.02477 0.02117 0.0141 0.0051 1.0000 10.000 1.0069 0.02676 0.02341 0.0151 0.0050 1.0000 10.250 1.0184 0.02924 0.02617 0.0163 0.0049 1.0000 10.500 1.0268 0.03199 0.02921 0.0174 0.0048 1.0000 10.750 1.0236 0.03619 0.03377 0.0188 0.0048 1.0000 11.000 1.0146 0.04068 0.03857 0.0197 0.0048 1.0000 11.250 0.9919 0.04557 0.04370 0.0208 0.0048 1.0000 11.750 0.8393 0.08870 0.08709 -0.0099 0.0054 1.0000 12.000 0.8296 0.09517 0.09356 -0.0133 0.0055 1.0000