XFOIL Version 6.96 Calculated polar for: AH 80-140 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.000 -0.2828 0.09298 0.08766 -0.0428 0.5880 0.0251 -9.750 -0.2836 0.08884 0.08351 -0.0448 0.5864 0.0259 -9.500 -0.2870 0.08422 0.07890 -0.0471 0.5850 0.0258 -9.250 -0.2939 0.07908 0.07378 -0.0498 0.5836 0.0258 -9.000 -0.3049 0.07333 0.06807 -0.0531 0.5824 0.0258 -8.750 -0.3258 0.06604 0.06085 -0.0583 0.5814 0.0256 -8.500 -0.3742 0.05524 0.04997 -0.0645 0.5810 0.0253 -8.250 -0.4238 0.04283 0.03701 -0.0658 0.5807 0.0253 -8.000 -0.4361 0.03644 0.03000 -0.0643 0.5793 0.0262 -7.750 -0.4406 0.03068 0.02329 -0.0621 0.5777 0.0274 -7.500 -0.4202 0.02967 0.02218 -0.0614 0.5754 0.0278 -7.250 -0.3999 0.02855 0.02089 -0.0607 0.5730 0.0283 -7.000 -0.3798 0.02717 0.01928 -0.0598 0.5707 0.0289 -6.750 -0.3591 0.02575 0.01755 -0.0589 0.5686 0.0296 -6.500 -0.3376 0.02432 0.01575 -0.0580 0.5666 0.0306 -6.250 -0.3146 0.02326 0.01441 -0.0572 0.5648 0.0316 -6.000 -0.2900 0.02266 0.01376 -0.0568 0.5630 0.0325 -5.750 -0.2653 0.02195 0.01294 -0.0562 0.5611 0.0336 -5.500 -0.2404 0.02110 0.01194 -0.0557 0.5591 0.0345 -5.250 -0.2152 0.02030 0.01093 -0.0551 0.5572 0.0357 -5.000 -0.1900 0.01970 0.01033 -0.0546 0.5551 0.0367 -4.750 -0.1644 0.01925 0.00983 -0.0542 0.5529 0.0383 -4.500 -0.1386 0.01875 0.00920 -0.0536 0.5509 0.0401 -4.250 -0.1132 0.01826 0.00867 -0.0531 0.5491 0.0417 -4.000 -0.0875 0.01786 0.00824 -0.0527 0.5474 0.0436 -3.750 -0.0617 0.01749 0.00776 -0.0521 0.5457 0.0458 -3.500 -0.0361 0.01713 0.00745 -0.0517 0.5436 0.0483 -3.250 -0.0101 0.01686 0.00716 -0.0512 0.5417 0.0518 -3.000 0.0158 0.01657 0.00691 -0.0508 0.5397 0.0551 -2.750 0.0420 0.01634 0.00663 -0.0504 0.5375 0.0592 -2.500 0.0679 0.01610 0.00641 -0.0499 0.5354 0.0641 -2.250 0.0939 0.01587 0.00618 -0.0495 0.5335 0.0700 -2.000 0.1202 0.01568 0.00598 -0.0491 0.5319 0.0778 -1.750 0.1464 0.01550 0.00581 -0.0487 0.5303 0.0878 -1.500 0.1725 0.01532 0.00566 -0.0483 0.5289 0.1026 -1.250 0.1985 0.01515 0.00555 -0.0479 0.5274 0.1268 -1.000 0.2235 0.01489 0.00551 -0.0474 0.5253 0.1732 -0.750 0.2476 0.01454 0.00550 -0.0468 0.5231 0.2589 -0.500 0.2699 0.01409 0.00548 -0.0459 0.5210 0.3811 -0.250 0.2883 0.01347 0.00555 -0.0441 0.5191 0.5668 0.000 0.3080 0.01302 0.00569 -0.0419 0.5172 0.7326 0.250 0.3402 0.01285 0.00579 -0.0421 0.5151 0.8491 0.500 0.3899 0.01285 0.00579 -0.0460 0.5127 0.9190 0.750 0.4452 0.01291 0.00575 -0.0512 0.5105 0.9590 1.000 0.5065 0.01303 0.00579 -0.0579 0.5081 0.9873 1.250 0.5523 0.01314 0.00588 -0.0617 0.5053 1.0000 1.500 0.5740 0.01325 0.00597 -0.0606 0.5027 1.0000 1.750 0.5963 0.01336 0.00604 -0.0596 0.5003 1.0000 2.000 0.6192 0.01348 0.00612 -0.0587 0.4981 1.0000 2.250 0.6427 0.01360 0.00619 -0.0579 0.4962 1.0000 2.500 0.6666 0.01372 0.00626 -0.0572 0.4943 1.0000 2.750 0.6910 0.01384 0.00632 -0.0565 0.4925 1.0000 3.000 0.7153 0.01400 0.00644 -0.0558 0.4904 1.0000 3.250 0.7385 0.01419 0.00669 -0.0550 0.4873 1.0000 3.500 0.7625 0.01437 0.00689 -0.0543 0.4844 1.0000 3.750 0.7869 0.01453 0.00707 -0.0537 0.4818 1.0000 4.000 0.8118 0.01466 0.00718 -0.0531 0.4792 1.0000 4.250 0.8372 0.01475 0.00724 -0.0526 0.4768 1.0000 4.500 0.8630 0.01483 0.00728 -0.0522 0.4746 1.0000 4.750 0.8870 0.01504 0.00755 -0.0515 0.4714 1.0000 5.000 0.9109 0.01527 0.00785 -0.0509 0.4679 1.0000 5.250 0.9355 0.01544 0.00806 -0.0504 0.4647 1.0000 5.500 0.9608 0.01554 0.00819 -0.0499 0.4617 1.0000 5.750 0.9867 0.01561 0.00824 -0.0495 0.4591 1.0000 6.000 1.0120 0.01573 0.00838 -0.0490 0.4560 1.0000 6.250 1.0351 0.01597 0.00874 -0.0484 0.4509 1.0000 6.500 1.0600 0.01603 0.00884 -0.0478 0.4462 1.0000 6.750 1.0860 0.01598 0.00877 -0.0474 0.4422 1.0000 7.000 1.1094 0.01619 0.00909 -0.0468 0.4367 1.0000 7.250 1.1334 0.01635 0.00932 -0.0462 0.4312 1.0000 7.500 1.1585 0.01641 0.00940 -0.0457 0.4271 1.0000 7.750 1.1823 0.01662 0.00970 -0.0452 0.4224 1.0000 8.000 1.2054 0.01686 0.01005 -0.0446 0.4165 1.0000 8.250 1.2299 0.01691 0.01010 -0.0440 0.4110 1.0000 8.500 1.2522 0.01716 0.01046 -0.0433 0.4030 1.0000 8.750 1.2755 0.01730 0.01062 -0.0426 0.3964 1.0000 9.000 1.2975 0.01758 0.01098 -0.0419 0.3898 1.0000 9.250 1.3191 0.01778 0.01121 -0.0410 0.3812 1.0000 9.500 1.3384 0.01810 0.01156 -0.0399 0.3686 1.0000 9.750 1.3562 0.01849 0.01195 -0.0386 0.3547 1.0000 10.000 1.3714 0.01901 0.01244 -0.0370 0.3384 1.0000 10.250 1.3843 0.01964 0.01305 -0.0353 0.3227 1.0000 10.500 1.3930 0.02047 0.01384 -0.0331 0.3058 1.0000 10.750 1.3962 0.02148 0.01482 -0.0303 0.2895 1.0000 11.000 1.3935 0.02287 0.01618 -0.0274 0.2732 1.0000 11.250 1.3885 0.02496 0.01826 -0.0259 0.2583 1.0000 11.500 1.3820 0.02778 0.02106 -0.0255 0.2423 1.0000 11.750 1.3765 0.03073 0.02400 -0.0253 0.2275 1.0000 12.000 1.3690 0.03390 0.02713 -0.0251 0.2134 1.0000 12.250 1.3638 0.03685 0.03007 -0.0249 0.2023 1.0000 12.500 1.3574 0.03992 0.03312 -0.0247 0.1911 1.0000 12.750 1.3507 0.04302 0.03621 -0.0244 0.1798 1.0000 13.000 1.3457 0.04598 0.03916 -0.0242 0.1688 1.0000 13.250 1.3412 0.04891 0.04210 -0.0240 0.1593 1.0000 13.500 1.3360 0.05198 0.04517 -0.0239 0.1505 1.0000 13.750 1.3329 0.05498 0.04817 -0.0239 0.1408 1.0000 14.000 1.3297 0.05810 0.05129 -0.0241 0.1294 1.0000 14.250 1.3256 0.06139 0.05457 -0.0243 0.1188 1.0000 14.500 1.3215 0.06475 0.05791 -0.0246 0.1088 1.0000 14.750 1.3171 0.06821 0.06137 -0.0250 0.0993 1.0000 15.000 1.3125 0.07174 0.06489 -0.0254 0.0886 1.0000 15.250 1.3074 0.07541 0.06855 -0.0259 0.0796 1.0000 15.500 1.3016 0.07923 0.07235 -0.0265 0.0718 1.0000 15.750 1.2965 0.08300 0.07612 -0.0271 0.0650 1.0000 16.000 1.2931 0.08663 0.07979 -0.0278 0.0585 1.0000 16.250 1.2884 0.09048 0.08366 -0.0285 0.0530 1.0000 16.500 1.2837 0.09440 0.08761 -0.0294 0.0496 1.0000