XFOIL Version 6.96 Calculated polar for: GOE 401 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.500 -0.3376 0.09792 0.09564 -0.0228 1.0000 0.0221 -8.250 -0.3417 0.09553 0.09329 -0.0237 1.0000 0.0222 -8.000 -0.3456 0.09318 0.09098 -0.0237 1.0000 0.0222 -7.750 -0.3450 0.08930 0.08714 -0.0228 1.0000 0.0224 -7.500 -0.3368 0.08638 0.08423 -0.0207 1.0000 0.0226 -7.250 -0.3332 0.08400 0.08189 -0.0201 1.0000 0.0229 -7.000 -0.3303 0.08163 0.07955 -0.0201 1.0000 0.0231 -6.750 -0.3283 0.07941 0.07736 -0.0200 1.0000 0.0233 -6.500 -0.3063 0.07580 0.07375 -0.0251 0.9975 0.0240 -6.250 -0.2743 0.07133 0.06925 -0.0330 0.9924 0.0250 -6.000 -0.1650 0.04656 0.04444 -0.0562 0.9530 0.0274 -5.750 -0.1398 0.04225 0.04011 -0.0594 0.9435 0.0278 -5.500 -0.1080 0.03838 0.03619 -0.0640 0.9315 0.0284 -5.250 -0.0734 0.03439 0.03211 -0.0699 0.9164 0.0293 -5.000 -0.0439 0.03078 0.02835 -0.0746 0.8960 0.0309 -4.750 -0.0085 0.02706 0.02430 -0.0805 0.8764 0.0332 -4.500 0.0085 0.02227 0.01930 -0.0824 0.8597 0.0337 -4.250 0.0252 0.02009 0.01702 -0.0822 0.8432 0.0342 -4.000 0.0443 0.01843 0.01528 -0.0822 0.8282 0.0348 -3.750 0.0651 0.01680 0.01353 -0.0822 0.8142 0.0357 -3.500 0.0873 0.01517 0.01176 -0.0825 0.8006 0.0371 -3.250 0.1199 0.01376 0.00998 -0.0830 0.7884 0.0410 -3.000 0.1376 0.01060 0.00662 -0.0833 0.7765 0.0423 -2.750 0.1593 0.00969 0.00562 -0.0830 0.7628 0.0432 -2.500 0.1821 0.00889 0.00471 -0.0827 0.7490 0.0447 -2.250 0.2204 0.02225 0.01766 -0.0881 0.7599 0.0477 -2.000 0.2448 0.01999 0.01505 -0.0871 0.7457 0.0523 -1.750 0.2682 0.01930 0.01428 -0.0865 0.7302 0.0538 -1.500 0.2924 0.01863 0.01347 -0.0858 0.7139 0.0568 -1.250 0.3171 0.01729 0.01181 -0.0847 0.6975 0.0639 -1.000 0.3410 0.01669 0.01114 -0.0840 0.6787 0.0659 -0.750 0.3673 0.01223 0.00568 -0.0815 0.6635 0.0417 -0.500 0.3926 0.01200 0.00530 -0.0806 0.6398 0.0412 -0.250 0.4169 0.01124 0.00435 -0.0796 0.6141 0.0408 0.000 0.4410 0.01083 0.00375 -0.0786 0.5844 0.0407 0.250 0.4651 0.01067 0.00342 -0.0776 0.5528 0.0409 0.500 0.4886 0.01038 0.00296 -0.0766 0.5243 0.0416 0.750 0.5125 0.01019 0.00265 -0.0756 0.5011 0.0418 1.000 0.5367 0.01005 0.00241 -0.0747 0.4839 0.0424 1.250 0.5614 0.00996 0.00225 -0.0739 0.4703 0.0437 1.500 0.5865 0.00994 0.00218 -0.0732 0.4590 0.0454 1.750 0.6117 0.00998 0.00216 -0.0725 0.4494 0.0476 2.000 0.6376 0.01000 0.00215 -0.0720 0.4406 0.0503 2.250 0.6628 0.01002 0.00220 -0.0713 0.4329 0.0671 2.500 0.6883 0.00996 0.00234 -0.0708 0.4253 0.1423 2.750 0.7134 0.01006 0.00245 -0.0702 0.4185 0.1809 3.000 0.7341 0.00937 0.00260 -0.0690 0.4123 0.5622 3.250 0.8089 0.00875 0.00280 -0.0797 0.4021 1.0000 3.500 0.8344 0.00886 0.00290 -0.0791 0.3958 1.0000 3.750 0.8589 0.00905 0.00301 -0.0783 0.3885 1.0000 4.000 0.8843 0.00915 0.00312 -0.0777 0.3806 1.0000 4.250 0.9088 0.00933 0.00324 -0.0770 0.3734 1.0000 4.500 0.9340 0.00946 0.00337 -0.0763 0.3670 1.0000 4.750 0.9587 0.00961 0.00350 -0.0757 0.3595 1.0000 5.000 0.9836 0.00975 0.00364 -0.0750 0.3511 1.0000 5.250 1.0079 0.00993 0.00378 -0.0742 0.3426 1.0000 5.500 1.0328 0.01006 0.00393 -0.0736 0.3343 1.0000 6.000 1.0816 0.01041 0.00429 -0.0722 0.3179 1.0000 6.250 1.1055 0.01062 0.00448 -0.0714 0.3088 1.0000 6.500 1.1292 0.01083 0.00467 -0.0706 0.2971 1.0000 6.750 1.1526 0.01106 0.00487 -0.0698 0.2827 1.0000 7.000 1.1756 0.01133 0.00510 -0.0689 0.2674 1.0000 7.250 1.1984 0.01162 0.00536 -0.0680 0.2535 1.0000 7.500 1.2206 0.01196 0.00566 -0.0671 0.2377 1.0000 7.750 1.2426 0.01232 0.00599 -0.0661 0.2200 1.0000 8.000 1.2637 0.01274 0.00635 -0.0650 0.2003 1.0000 8.250 1.2829 0.01333 0.00680 -0.0636 0.1716 1.0000 8.500 1.2968 0.01439 0.00753 -0.0615 0.1172 1.0000 8.750 1.3052 0.01590 0.00868 -0.0587 0.0645 1.0000 9.000 1.3215 0.01669 0.00945 -0.0569 0.0536 1.0000 9.250 1.3374 0.01748 0.01023 -0.0551 0.0436 1.0000 9.500 1.3535 0.01822 0.01096 -0.0533 0.0333 1.0000 9.750 1.3674 0.01908 0.01179 -0.0511 0.0274 1.0000 10.000 1.3826 0.01978 0.01255 -0.0492 0.0245 1.0000 10.250 1.3924 0.02079 0.01360 -0.0465 0.0221 1.0000 10.500 1.4040 0.02151 0.01440 -0.0441 0.0210 1.0000 10.750 1.4125 0.02231 0.01527 -0.0411 0.0199 1.0000 11.000 1.4191 0.02324 0.01628 -0.0381 0.0190 1.0000 11.250 1.4230 0.02438 0.01749 -0.0350 0.0184 1.0000 11.500 1.4183 0.02612 0.01934 -0.0313 0.0176 1.0000 11.750 1.4163 0.02789 0.02123 -0.0285 0.0172 1.0000 12.000 1.4210 0.02935 0.02279 -0.0267 0.0168 1.0000 12.250 1.4219 0.03125 0.02481 -0.0251 0.0164 1.0000 12.500 1.4223 0.03337 0.02704 -0.0238 0.0161 1.0000 12.750 1.4234 0.03559 0.02936 -0.0229 0.0156 1.0000 13.000 1.4224 0.03818 0.03204 -0.0222 0.0153 1.0000 13.250 1.4212 0.04094 0.03490 -0.0219 0.0149 1.0000 13.500 1.4181 0.04404 0.03809 -0.0218 0.0146 1.0000 13.750 1.4133 0.04745 0.04159 -0.0220 0.0143 1.0000 14.000 1.4083 0.05095 0.04519 -0.0221 0.0142 1.0000 14.250 1.4011 0.05476 0.04910 -0.0224 0.0140 1.0000 14.500 1.3890 0.05900 0.05343 -0.0223 0.0136 1.0000 14.750 1.3844 0.06249 0.05702 -0.0223 0.0135 1.0000 15.000 1.3830 0.06584 0.06048 -0.0229 0.0134 1.0000 15.250 1.3809 0.06936 0.06412 -0.0236 0.0132 1.0000 15.500 1.3785 0.07295 0.06783 -0.0243 0.0131 1.0000 15.750 1.3760 0.07664 0.07164 -0.0251 0.0129 1.0000 16.000 1.3722 0.08047 0.07558 -0.0258 0.0127 1.0000 16.250 1.3692 0.08425 0.07949 -0.0267 0.0127 1.0000 16.500 1.3652 0.08832 0.08368 -0.0278 0.0125 1.0000 16.750 1.3604 0.09259 0.08807 -0.0291 0.0123 1.0000 17.000 1.3555 0.09692 0.09252 -0.0305 0.0121 1.0000 17.250 1.3496 0.10152 0.09724 -0.0321 0.0120 1.0000 17.500 1.3445 0.10612 0.10195 -0.0340 0.0118 1.0000 17.750 1.3379 0.11099 0.10694 -0.0360 0.0117 1.0000 18.000 1.3314 0.11596 0.11203 -0.0382 0.0116 1.0000 18.250 1.3213 0.12170 0.11793 -0.0408 0.0116 1.0000 18.500 1.3161 0.12672 0.12302 -0.0435 0.0113 1.0000 18.750 1.3076 0.13242 0.12885 -0.0465 0.0112 1.0000 19.000 1.3009 0.13784 0.13436 -0.0495 0.0111 1.0000