XFOIL Version 6.96 Calculated polar for: GOE 683 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.9573 0.09230 0.08799 -0.0630 1.0000 0.0389 -19.500 -0.9678 0.08755 0.08319 -0.0654 1.0000 0.0393 -19.250 -0.9785 0.08287 0.07845 -0.0677 1.0000 0.0395 -19.000 -0.9904 0.07800 0.07352 -0.0701 1.0000 0.0399 -18.750 -1.0022 0.07321 0.06864 -0.0724 1.0000 0.0402 -18.500 -1.0134 0.06860 0.06395 -0.0746 1.0000 0.0404 -18.250 -1.0237 0.06416 0.05942 -0.0766 1.0000 0.0408 -18.000 -1.0329 0.05996 0.05512 -0.0785 1.0000 0.0411 -17.750 -1.0397 0.05610 0.05117 -0.0801 1.0000 0.0415 -17.500 -1.0449 0.05254 0.04751 -0.0815 1.0000 0.0420 -17.250 -1.0510 0.04904 0.04391 -0.0826 1.0000 0.0421 -17.000 -1.0531 0.04606 0.04083 -0.0835 1.0000 0.0426 -16.750 -1.0543 0.04332 0.03799 -0.0840 1.0000 0.0430 -16.500 -1.0548 0.04080 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0.00328 -0.0383 0.4899 0.2459 -1.750 0.0968 0.01122 0.00325 -0.0369 0.4839 0.2585 -1.500 0.1190 0.01116 0.00322 -0.0356 0.4778 0.2730 -1.250 0.1402 0.01110 0.00320 -0.0342 0.4713 0.2875 -1.000 0.1609 0.01108 0.00318 -0.0327 0.4653 0.3019 -0.750 0.1827 0.01101 0.00317 -0.0314 0.4599 0.3198 -0.500 0.2034 0.01093 0.00316 -0.0299 0.4546 0.3438 -0.250 0.2228 0.01087 0.00317 -0.0282 0.4491 0.3711 0.000 0.2416 0.01072 0.00318 -0.0263 0.4447 0.4155 0.250 0.2593 0.01057 0.00319 -0.0242 0.4398 0.4611 0.500 0.2754 0.01046 0.00321 -0.0218 0.4350 0.5043 0.750 0.2890 0.01035 0.00324 -0.0188 0.4309 0.5490 1.000 0.3020 0.01023 0.00328 -0.0156 0.4273 0.5930 1.250 0.3142 0.01009 0.00331 -0.0122 0.4237 0.6394 1.500 0.3255 0.00995 0.00334 -0.0086 0.4193 0.6880 1.750 0.3466 0.00975 0.00341 -0.0072 0.4151 0.7576 2.000 0.5048 0.01050 0.00444 -0.0347 0.4056 0.8548 2.250 0.5415 0.01086 0.00479 -0.0363 0.3992 0.8755 2.500 0.5673 0.01116 0.00506 -0.0357 0.3947 0.8892 2.750 0.5899 0.01140 0.00528 -0.0344 0.3912 0.9001 3.000 0.6072 0.01158 0.00546 -0.0321 0.3876 0.9116 3.250 0.6382 0.01190 0.00576 -0.0326 0.3828 0.9190 3.500 0.6571 0.01214 0.00597 -0.0306 0.3787 0.9270 3.750 0.6919 0.01245 0.00624 -0.0321 0.3740 0.9304 4.000 0.7195 0.01266 0.00646 -0.0320 0.3709 0.9354 4.250 0.7380 0.01285 0.00665 -0.0300 0.3676 0.9412 4.500 0.7750 0.01310 0.00688 -0.0320 0.3629 0.9433 4.750 0.8048 0.01334 0.00708 -0.0325 0.3583 0.9459 5.000 0.8309 0.01358 0.00731 -0.0322 0.3549 0.9506 5.250 0.8555 0.01381 0.00755 -0.0316 0.3514 0.9554 5.500 0.8924 0.01400 0.00774 -0.0336 0.3470 0.9571 5.750 0.9237 0.01420 0.00792 -0.0346 0.3430 0.9593 6.000 0.9501 0.01443 0.00813 -0.0345 0.3385 0.9625 6.250 0.9605 0.01467 0.00840 -0.0310 0.3358 0.9677 6.500 0.9896 0.01478 0.00851 -0.0316 0.3311 0.9686 6.750 1.0145 0.01493 0.00864 -0.0313 0.3259 0.9698 7.000 1.0354 0.01509 0.00879 -0.0303 0.3219 0.9712 7.250 1.0570 0.01520 0.00893 -0.0293 0.3183 0.9728 7.500 1.0766 0.01537 0.00911 -0.0280 0.3140 0.9751 7.750 1.0892 0.01559 0.00934 -0.0253 0.3102 0.9778 8.000 1.0963 0.01590 0.00964 -0.0216 0.3066 0.9806 8.250 1.1204 0.01604 0.00980 -0.0213 0.3033 0.9814 8.500 1.1447 0.01621 0.01000 -0.0212 0.2993 0.9825 8.750 1.1654 0.01645 0.01026 -0.0204 0.2950 0.9838 9.000 1.1826 0.01677 0.01057 -0.0190 0.2909 0.9853 9.250 1.2001 0.01707 0.01090 -0.0177 0.2865 0.9867 9.500 1.2167 0.01741 0.01126 -0.0163 0.2819 0.9882 9.750 1.2279 0.01796 0.01180 -0.0142 0.2748 0.9902 10.000 1.2412 0.01848 0.01234 -0.0124 0.2705 0.9920 10.250 1.2587 0.01892 0.01280 -0.0115 0.2653 0.9929 10.500 1.2742 0.01951 0.01340 -0.0106 0.2596 0.9940 10.750 1.2897 0.02013 0.01403 -0.0097 0.2546 0.9951 11.000 1.3057 0.02073 0.01467 -0.0089 0.2495 0.9962 11.250 1.3174 0.02161 0.01556 -0.0078 0.2430 0.9974 11.500 1.3318 0.02248 0.01644 -0.0072 0.2359 0.9986 11.750 1.3442 0.02357 0.01752 -0.0066 0.2280 0.9996 12.000 1.3503 0.02472 0.01869 -0.0049 0.2205 1.0000 12.250 1.3506 0.02601 0.01998 -0.0023 0.2132 1.0000 12.500 1.3499 0.02744 0.02143 0.0002 0.2056 1.0000 12.750 1.3468 0.02912 0.02309 0.0026 0.1968 1.0000 13.000 1.3433 0.03091 0.02489 0.0049 0.1867 1.0000 13.250 1.3342 0.03322 0.02717 0.0073 0.1740 1.0000 13.500 1.3236 0.03577 0.02970 0.0095 0.1615 1.0000 13.750 1.3093 0.03876 0.03265 0.0116 0.1491 1.0000 14.000 1.2971 0.04174 0.03563 0.0134 0.1406 1.0000 14.250 1.2880 0.04459 0.03849 0.0148 0.1346 1.0000 14.500 1.2814 0.04729 0.04123 0.0160 0.1311 1.0000 14.750 1.2762 0.04997 0.04395 0.0170 0.1278 1.0000 15.000 1.2706 0.05276 0.04678 0.0178 0.1247 1.0000 15.250 1.2645 0.05565 0.04972 0.0186 0.1222 1.0000 15.500 1.2575 0.05872 0.05282 0.0192 0.1196 1.0000 15.750 1.2525 0.06166 0.05581 0.0197 0.1174 1.0000 16.000 1.2509 0.06428 0.05851 0.0201 0.1157 1.0000 16.250 1.2488 0.06697 0.06125 0.0205 0.1139 1.0000 16.500 1.2427 0.07016 0.06448 0.0207 0.1113 1.0000 16.750 1.2374 0.07331 0.06767 0.0209 0.1094 1.0000 17.000 1.2336 0.07633 0.07073 0.0210 0.1080 1.0000 17.250 1.2276 0.07964 0.07409 0.0210 0.1063 1.0000 17.500 1.2303 0.08192 0.07644 0.0211 0.1051 1.0000 17.750 1.2307 0.08452 0.07911 0.0210 0.1034 1.0000 18.000 1.2304 0.08722 0.08186 0.0210 0.1017 1.0000 18.250 1.2295 0.09000 0.08469 0.0208 0.0999 1.0000 18.500 1.2273 0.09298 0.08772 0.0206 0.0985 1.0000 18.750 1.2254 0.09592 0.09069 0.0203 0.0971 1.0000