XFOIL Version 6.96 Calculated polar for: GOE 368 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.3779 0.09785 0.09149 -0.0103 1.0000 0.0588 -7.500 -0.3757 0.09430 0.08803 -0.0116 1.0000 0.0545 -7.250 -0.3806 0.09046 0.08431 -0.0169 1.0000 0.0485 -7.000 -0.3726 0.08688 0.08079 -0.0168 1.0000 0.0468 -6.750 -0.3657 0.08327 0.07725 -0.0184 1.0000 0.0452 -6.250 -0.3507 0.07514 0.06918 -0.0238 1.0000 0.0422 -6.000 -0.3408 0.07038 0.06445 -0.0277 1.0000 0.0406 -5.500 -0.3110 0.05902 0.05296 -0.0372 1.0000 0.0376 -5.250 -0.2954 0.05456 0.04844 -0.0395 1.0000 0.0372 -5.000 -0.2774 0.04958 0.04332 -0.0422 1.0000 0.0368 -4.750 -0.2565 0.04379 0.03726 -0.0453 1.0000 0.0366 -4.500 -0.2330 0.03808 0.03101 -0.0483 1.0000 0.0371 -4.250 -0.2085 0.03334 0.02559 -0.0500 1.0000 0.0383 -4.000 -0.1866 0.03053 0.02250 -0.0502 1.0000 0.0405 -3.750 -0.1627 0.02789 0.01940 -0.0502 1.0000 0.0422 -3.500 -0.1385 0.02567 0.01674 -0.0498 1.0000 0.0443 -3.250 -0.1142 0.02396 0.01462 -0.0491 1.0000 0.0475 -3.000 -0.0904 0.02254 0.01303 -0.0487 1.0000 0.0552 -2.750 -0.0670 0.02148 0.01189 -0.0479 1.0000 0.0652 -2.500 -0.0448 0.02115 0.01184 -0.0470 1.0000 0.0940 -2.250 -0.0062 0.02280 0.01333 -0.0496 0.9839 0.1807 -2.000 0.0363 0.02353 0.01382 -0.0530 0.9631 0.2310 -1.750 0.0794 0.02279 0.01271 -0.0558 0.9436 0.2347 -1.500 0.1238 0.02215 0.01171 -0.0587 0.9247 0.2395 -1.250 0.1646 0.02163 0.01087 -0.0608 0.9024 0.2463 -1.000 0.2073 0.02109 0.01010 -0.0631 0.8812 0.2532 -0.750 0.2478 0.02064 0.00937 -0.0648 0.8580 0.2594 -0.500 0.2850 0.02020 0.00880 -0.0659 0.8337 0.2664 -0.250 0.3188 0.01990 0.00834 -0.0662 0.8085 0.2755 0.000 0.3487 0.01969 0.00799 -0.0659 0.7820 0.2880 0.250 0.3759 0.01951 0.00773 -0.0651 0.7545 0.3021 0.500 0.4016 0.01933 0.00751 -0.0641 0.7264 0.3178 0.750 0.4266 0.01913 0.00731 -0.0630 0.6980 0.3398 1.000 0.4510 0.01884 0.00714 -0.0619 0.6702 0.3815 1.250 0.4809 0.01747 0.00693 -0.0612 0.6416 1.0000 1.500 0.5058 0.01778 0.00689 -0.0600 0.6139 1.0000 1.750 0.5303 0.01810 0.00692 -0.0589 0.5864 1.0000 2.000 0.5547 0.01842 0.00702 -0.0579 0.5593 1.0000 2.250 0.5791 0.01873 0.00716 -0.0570 0.5330 1.0000 2.500 0.6034 0.01906 0.00729 -0.0560 0.5084 1.0000 2.750 0.6279 0.01940 0.00747 -0.0552 0.4850 1.0000 3.000 0.6528 0.01979 0.00770 -0.0544 0.4637 1.0000 3.250 0.6776 0.02023 0.00803 -0.0538 0.4436 1.0000 3.500 0.7026 0.02071 0.00837 -0.0531 0.4255 1.0000 3.750 0.7277 0.02123 0.00880 -0.0526 0.4082 1.0000 4.000 0.7527 0.02179 0.00936 -0.0520 0.3913 1.0000 4.250 0.7776 0.02237 0.00992 -0.0515 0.3760 1.0000 4.500 0.8026 0.02298 0.01053 -0.0510 0.3624 1.0000 4.750 0.8277 0.02362 0.01121 -0.0505 0.3509 1.0000 5.000 0.8527 0.02429 0.01199 -0.0500 0.3395 1.0000 5.250 0.8775 0.02499 0.01282 -0.0496 0.3290 1.0000 5.500 0.9024 0.02570 0.01359 -0.0490 0.3201 1.0000 5.750 0.9269 0.02644 0.01455 -0.0485 0.3112 1.0000 6.000 0.9516 0.02724 0.01554 -0.0480 0.3037 1.0000 6.250 0.9763 0.02809 0.01660 -0.0476 0.2973 1.0000 6.500 0.9981 0.02856 0.01723 -0.0467 0.2840 1.0000 6.750 1.0136 0.02831 0.01695 -0.0451 0.2543 1.0000 7.000 1.0342 0.02879 0.01760 -0.0441 0.2394 1.0000 7.250 1.0538 0.02929 0.01834 -0.0430 0.2231 1.0000 7.500 1.0733 0.02990 0.01917 -0.0420 0.2051 1.0000 7.750 1.0911 0.03056 0.01996 -0.0410 0.1801 1.0000 8.000 1.1101 0.03140 0.02099 -0.0400 0.1499 1.0000 8.250 1.1143 0.03417 0.02295 -0.0387 0.0440 1.0000 8.500 1.1219 0.03688 0.02573 -0.0372 0.0351 1.0000 9.000 1.1311 0.04217 0.03148 -0.0345 0.0294 1.0000 9.250 1.1309 0.04493 0.03450 -0.0332 0.0281 1.0000 9.500 1.1245 0.04791 0.03772 -0.0318 0.0275 1.0000 9.750 1.1158 0.05142 0.04146 -0.0315 0.0272 1.0000 10.000 1.1043 0.05585 0.04612 -0.0326 0.0269 1.0000 10.250 1.0933 0.06086 0.05136 -0.0348 0.0268 1.0000 10.500 1.0811 0.06653 0.05723 -0.0376 0.0267 1.0000 10.750 1.0708 0.07212 0.06301 -0.0403 0.0267 1.0000 11.000 1.0605 0.07782 0.06886 -0.0429 0.0266 1.0000 11.250 1.0516 0.08329 0.07445 -0.0452 0.0265 1.0000 11.500 1.0450 0.08829 0.07956 -0.0472 0.0264 1.0000 11.750 1.0397 0.09300 0.08437 -0.0489 0.0262 1.0000 12.000 1.0359 0.09738 0.08883 -0.0502 0.0258 1.0000