XFOIL Version 6.96 Calculated polar for: S8066 (10% version of S8065 w/ lower surface aer 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.250 -0.6786 0.04136 0.03625 -0.0271 1.0000 0.0351 -7.000 -0.6813 0.03628 0.03097 -0.0241 1.0000 0.0319 -6.750 -0.6773 0.03172 0.02544 -0.0193 1.0000 0.0264 -6.500 -0.6646 0.02915 0.02258 -0.0171 1.0000 0.0257 -6.250 -0.6512 0.02635 0.01944 -0.0150 1.0000 0.0254 -6.000 -0.6346 0.02423 0.01699 -0.0130 1.0000 0.0254 -5.750 -0.6161 0.02256 0.01507 -0.0114 1.0000 0.0256 -5.500 -0.5966 0.02122 0.01354 -0.0098 1.0000 0.0262 -5.250 -0.5784 0.01898 0.01123 -0.0083 1.0000 0.0284 -5.000 -0.5592 0.01833 0.01056 -0.0070 1.0000 0.0319 -4.750 -0.5287 0.01728 0.00937 -0.0077 0.9974 0.0363 -4.500 -0.4970 0.01584 0.00797 -0.0089 0.9943 0.0497 -4.250 -0.4665 0.01486 0.00715 -0.0100 0.9902 0.0885 -4.000 -0.4343 0.01405 0.00669 -0.0117 0.9863 0.1505 -3.750 -0.4029 0.01289 0.00625 -0.0135 0.9830 0.2951 -3.500 -0.3797 0.01190 0.00608 -0.0134 0.9775 0.4793 -3.250 -0.3496 0.01150 0.00613 -0.0139 0.9730 0.6010 -3.000 -0.3174 0.01145 0.00634 -0.0145 0.9691 0.6858 -2.750 -0.2905 0.01149 0.00641 -0.0140 0.9629 0.7332 -2.500 -0.2559 0.01160 0.00650 -0.0151 0.9586 0.7706 -2.250 -0.2255 0.01171 0.00661 -0.0153 0.9536 0.7994 -2.000 -0.1970 0.01180 0.00669 -0.0150 0.9476 0.8238 -1.750 -0.1611 0.01189 0.00675 -0.0162 0.9440 0.8460 -1.500 -0.1354 0.01199 0.00683 -0.0153 0.9376 0.8669 -1.250 -0.1039 0.01207 0.00690 -0.0155 0.9325 0.8869 -1.000 -0.0644 0.01219 0.00699 -0.0172 0.9298 0.9044 -0.750 -0.0316 0.01230 0.00708 -0.0178 0.9244 0.9197 -0.500 0.0090 0.01238 0.00712 -0.0201 0.9200 0.9311 -0.250 0.0559 0.01241 0.00711 -0.0237 0.9173 0.9392 0.000 0.1057 0.01240 0.00708 -0.0280 0.9152 0.9448 0.250 0.1500 0.01242 0.00710 -0.0314 0.9100 0.9508 0.500 0.1928 0.01235 0.00703 -0.0343 0.9047 0.9572 0.750 0.2451 0.01219 0.00688 -0.0391 0.9015 0.9596 1.000 0.2875 0.01208 0.00680 -0.0420 0.8938 0.9648 1.250 0.3264 0.01185 0.00659 -0.0438 0.8870 0.9708 1.500 0.3679 0.01162 0.00641 -0.0464 0.8768 0.9753 1.750 0.4049 0.01136 0.00619 -0.0479 0.8661 0.9815 2.000 0.4426 0.01101 0.00588 -0.0495 0.8538 0.9869 2.250 0.4788 0.01066 0.00557 -0.0507 0.8383 0.9931 2.500 0.5158 0.01027 0.00523 -0.0522 0.8195 0.9990 2.750 0.5368 0.01000 0.00496 -0.0506 0.8006 1.0000 3.000 0.5539 0.00982 0.00483 -0.0483 0.7783 1.0000 3.250 0.5720 0.00966 0.00465 -0.0462 0.7541 1.0000 3.500 0.5900 0.00956 0.00454 -0.0440 0.7265 1.0000 3.750 0.6075 0.00955 0.00448 -0.0418 0.6929 1.0000 4.000 0.6239 0.00964 0.00444 -0.0393 0.6475 1.0000 4.250 0.6388 0.00988 0.00446 -0.0366 0.5883 1.0000 4.500 0.6509 0.01035 0.00458 -0.0335 0.5049 1.0000 4.750 0.6591 0.01118 0.00488 -0.0300 0.3912 1.0000 5.000 0.6662 0.01232 0.00537 -0.0267 0.2687 1.0000 5.250 0.6758 0.01357 0.00602 -0.0239 0.1686 1.0000 5.500 0.6900 0.01461 0.00674 -0.0218 0.1230 1.0000 5.750 0.7069 0.01549 0.00751 -0.0200 0.1016 1.0000 6.000 0.7247 0.01638 0.00836 -0.0183 0.0880 1.0000 6.250 0.7430 0.01731 0.00927 -0.0168 0.0772 1.0000 6.500 0.7618 0.01829 0.01017 -0.0155 0.0668 1.0000 6.750 0.7836 0.01878 0.01076 -0.0146 0.0573 1.0000 7.000 0.8032 0.01990 0.01193 -0.0133 0.0492 1.0000 7.250 0.8221 0.02125 0.01326 -0.0121 0.0411 1.0000 7.500 0.8437 0.02234 0.01447 -0.0110 0.0358 1.0000 7.750 0.8651 0.02498 0.01716 -0.0102 0.0321 1.0000 8.000 0.8877 0.02673 0.01917 -0.0091 0.0306 1.0000 8.250 0.9084 0.02838 0.02111 -0.0079 0.0284 1.0000 8.500 0.9276 0.02989 0.02280 -0.0068 0.0265 1.0000 8.750 0.9448 0.03189 0.02503 -0.0054 0.0254 1.0000 9.000 0.9595 0.03449 0.02793 -0.0039 0.0248 1.0000 9.250 0.9701 0.03761 0.03139 -0.0019 0.0245 1.0000 9.500 0.9742 0.04155 0.03583 0.0009 0.0249 1.0000 9.750 0.9529 0.04877 0.04391 0.0061 0.0271 1.0000 10.000 0.9362 0.05387 0.04940 0.0096 0.0284 1.0000 10.250 0.9174 0.05782 0.05359 0.0131 0.0292 1.0000 10.500 0.8988 0.06153 0.05746 0.0154 0.0299 1.0000 10.750 0.8786 0.06573 0.06180 0.0166 0.0305 1.0000 11.000 0.8585 0.07054 0.06671 0.0164 0.0311 1.0000 11.250 0.7535 0.06806 0.06466 0.0162 0.0298 1.0000 11.500 0.7254 0.07571 0.07242 0.0122 0.0301 1.0000 11.750 0.6967 0.08497 0.08178 0.0066 0.0305 1.0000 12.000 0.6718 0.09480 0.09164 0.0011 0.0312 1.0000 12.500 0.7355 0.12843 0.12498 -0.0136 0.0537 1.0000 12.750 0.6225 0.12857 0.12540 -0.0108 0.0540 1.0000 13.000 0.6155 0.13388 0.13071 -0.0139 0.0539 1.0000