XFOIL Version 6.96 Calculated polar for: GOE 604 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 ------ -------- --------- --------- -------- -------- -------- -19.000 -0.6750 0.12238 0.12006 -0.0473 1.0000 0.0202 -18.750 -0.7020 0.11355 0.11113 -0.0524 1.0000 0.0206 -18.500 -0.7304 0.10487 0.10233 -0.0575 1.0000 0.0207 -18.250 -0.7540 0.09724 0.09460 -0.0620 1.0000 0.0209 -18.000 -0.7756 0.09013 0.08738 -0.0663 1.0000 0.0210 -17.750 -0.7965 0.08333 0.08048 -0.0703 1.0000 0.0212 -17.500 -0.8173 0.07678 0.07384 -0.0743 1.0000 0.0213 -17.250 -0.8416 0.07020 0.06715 -0.0783 1.0000 0.0214 -17.000 -0.8663 0.06358 0.06042 -0.0824 1.0000 0.0216 -16.750 -0.8877 0.05748 0.05421 -0.0861 1.0000 0.0217 -16.500 -0.9084 0.05151 0.04813 -0.0898 1.0000 0.0217 -16.250 -0.9256 0.04585 0.04234 -0.0935 1.0000 0.0218 -16.000 -0.9386 0.04058 0.03695 -0.0972 1.0000 0.0219 -15.750 -0.9462 0.03629 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-0.0727 0.4546 0.2141 -1.250 0.3463 0.00898 0.00238 -0.0723 0.4493 0.2348 -1.000 0.3715 0.00893 0.00239 -0.0716 0.4435 0.2627 -0.750 0.3980 0.00883 0.00238 -0.0713 0.4394 0.2940 -0.500 0.4241 0.00876 0.00239 -0.0708 0.4342 0.3230 -0.250 0.4496 0.00875 0.00240 -0.0702 0.4284 0.3472 0.000 0.4757 0.00871 0.00242 -0.0698 0.4235 0.3725 0.250 0.5016 0.00865 0.00244 -0.0693 0.4182 0.4028 0.500 0.5262 0.00862 0.00247 -0.0686 0.4123 0.4398 0.750 0.5505 0.00853 0.00251 -0.0678 0.4071 0.4899 1.000 0.5738 0.00839 0.00255 -0.0669 0.4009 0.5599 1.250 0.5943 0.00827 0.00262 -0.0654 0.3936 0.6433 1.500 0.6141 0.00806 0.00269 -0.0636 0.3882 0.7360 1.750 0.6327 0.00790 0.00279 -0.0615 0.3824 0.8262 2.000 0.6596 0.00789 0.00295 -0.0611 0.3759 0.9065 2.250 0.7160 0.00805 0.00313 -0.0670 0.3701 0.9507 2.500 0.7638 0.00826 0.00328 -0.0713 0.3639 0.9644 2.750 0.8042 0.00846 0.00342 -0.0740 0.3582 0.9722 3.000 0.8381 0.00861 0.00354 -0.0752 0.3537 0.9810 3.250 0.8792 0.00881 0.00368 -0.0780 0.3484 0.9859 3.500 0.9157 0.00903 0.00385 -0.0800 0.3429 0.9909 3.750 0.9546 0.00916 0.00396 -0.0824 0.3398 0.9943 4.000 0.9970 0.00931 0.00407 -0.0855 0.3361 0.9975 4.250 1.0365 0.00948 0.00420 -0.0881 0.3323 0.9997 4.500 1.0584 0.00965 0.00434 -0.0871 0.3286 1.0000 4.750 1.0774 0.00978 0.00445 -0.0854 0.3261 1.0000 5.000 1.0975 0.00987 0.00455 -0.0840 0.3242 1.0000 5.250 1.1172 0.00999 0.00467 -0.0824 0.3218 1.0000 5.500 1.1364 0.01012 0.00479 -0.0808 0.3193 1.0000 5.750 1.1549 0.01028 0.00494 -0.0790 0.3164 1.0000 6.000 1.1722 0.01048 0.00511 -0.0771 0.3131 1.0000 6.250 1.1906 0.01065 0.00527 -0.0753 0.3102 1.0000 6.500 1.2111 0.01076 0.00540 -0.0740 0.3083 1.0000 6.750 1.2307 0.01090 0.00555 -0.0725 0.3061 1.0000 7.000 1.2483 0.01105 0.00570 -0.0706 0.3038 1.0000 7.250 1.2637 0.01122 0.00587 -0.0683 0.3015 1.0000 7.500 1.2791 0.01141 0.00606 -0.0660 0.2992 1.0000 7.750 1.2940 0.01166 0.00629 -0.0637 0.2964 1.0000 8.000 1.3121 0.01185 0.00650 -0.0621 0.2945 1.0000 8.250 1.3325 0.01199 0.00667 -0.0609 0.2926 1.0000 8.500 1.3524 0.01217 0.00687 -0.0596 0.2901 1.0000 8.750 1.3713 0.01239 0.00710 -0.0583 0.2875 1.0000 9.000 1.3895 0.01265 0.00737 -0.0568 0.2848 1.0000 9.250 1.4063 0.01297 0.00768 -0.0553 0.2818 1.0000 9.500 1.4241 0.01328 0.00801 -0.0539 0.2790 1.0000 9.750 1.4450 0.01349 0.00826 -0.0530 0.2770 1.0000 10.000 1.4647 0.01376 0.00855 -0.0520 0.2743 1.0000 10.250 1.4830 0.01409 0.00889 -0.0509 0.2708 1.0000 10.500 1.4987 0.01454 0.00933 -0.0494 0.2666 1.0000 10.750 1.5169 0.01490 0.00972 -0.0484 0.2619 1.0000 11.000 1.5348 0.01530 0.01013 -0.0473 0.2569 1.0000 11.250 1.5475 0.01595 0.01075 -0.0457 0.2498 1.0000 11.500 1.5643 0.01644 0.01126 -0.0447 0.2424 1.0000 11.750 1.5754 0.01724 0.01203 -0.0431 0.2347 1.0000 12.000 1.5823 0.01832 0.01304 -0.0412 0.2196 1.0000 12.250 1.5822 0.01987 0.01450 -0.0388 0.2004 1.0000 12.500 1.5810 0.02164 0.01621 -0.0366 0.1870 1.0000 12.750 1.5809 0.02345 0.01800 -0.0349 0.1782 1.0000 13.000 1.5829 0.02526 0.01981 -0.0335 0.1723 1.0000 13.250 1.5829 0.02732 0.02189 -0.0323 0.1671 1.0000 13.500 1.5895 0.02894 0.02355 -0.0316 0.1647 1.0000 13.750 1.5945 0.03075 0.02542 -0.0309 0.1626 1.0000 14.000 1.5957 0.03295 0.02765 -0.0302 0.1600 1.0000 14.250 1.5944 0.03544 0.03019 -0.0296 0.1575 1.0000 14.500 1.5907 0.03823 0.03303 -0.0290 0.1547 1.0000 14.750 1.5941 0.04038 0.03525 -0.0287 0.1534 1.0000 15.000 1.5992 0.04238 0.03731 -0.0284 0.1521 1.0000 15.250 1.6006 0.04476 0.03975 -0.0282 0.1502 1.0000 15.500 1.5996 0.04742 0.04247 -0.0279 0.1486 1.0000 15.750 1.5959 0.05039 0.04549 -0.0277 0.1469 1.0000 16.000 1.5907 0.05355 0.04872 -0.0276 0.1453 1.0000 16.250 1.5831 0.05702 0.05224 -0.0275 0.1433 1.0000 16.500 1.5753 0.06055 0.05583 -0.0275 0.1415 1.0000 16.750 1.5775 0.06303 0.05838 -0.0276 0.1407 1.0000 17.000 1.5819 0.06529 0.06071 -0.0277 0.1394 1.0000 17.250 1.5827 0.06798 0.06347 -0.0279 0.1379 1.0000 17.500 1.5808 0.07099 0.06654 -0.0281 0.1361 1.0000 17.750 1.5769 0.07422 0.06982 -0.0284 0.1341 1.0000 18.000 1.5693 0.07796 0.07362 -0.0288 0.1322 1.0000 18.250 1.5604 0.08189 0.07758 -0.0293 0.1300 1.0000 18.500 1.5592 0.08492 0.08069 -0.0297 0.1281 1.0000 18.750 1.5613 0.08753 0.08336 -0.0301 0.1259 1.0000 19.000 1.5580 0.09084 0.08673 -0.0307 0.1238 1.0000 19.250 1.5499 0.09479 0.09071 -0.0314 0.1205 1.0000