XFOIL Version 6.96 Calculated polar for: GOE 735 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 ------ -------- --------- --------- -------- -------- -------- -19.250 -0.9242 0.09342 0.08983 -0.0458 1.0000 0.0419 -19.000 -0.9475 0.08623 0.08251 -0.0503 1.0000 0.0422 -18.750 -0.9709 0.07913 0.07528 -0.0548 1.0000 0.0426 -18.500 -0.9917 0.07269 0.06871 -0.0588 1.0000 0.0429 -18.250 -1.0108 0.06650 0.06238 -0.0627 1.0000 0.0433 -18.000 -1.0273 0.06080 0.05654 -0.0663 1.0000 0.0437 -17.750 -1.0404 0.05565 0.05124 -0.0695 1.0000 0.0440 -17.500 -1.0503 0.05115 0.04658 -0.0722 1.0000 0.0443 -17.250 -1.0582 0.04735 0.04274 -0.0738 1.0000 0.0448 -17.000 -1.0640 0.04387 0.03922 -0.0754 1.0000 0.0453 -16.750 -1.0673 0.04081 0.03611 -0.0765 1.0000 0.0458 -16.500 -1.0686 0.03816 0.03340 -0.0772 1.0000 0.0463 -16.250 -1.0680 0.03587 0.03104 -0.0774 1.0000 0.0470 -16.000 -1.0653 0.03389 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0.00417 -0.0150 0.4547 0.1827 -1.750 0.0703 0.01201 0.00409 -0.0144 0.4503 0.1949 -1.500 0.0949 0.01191 0.00405 -0.0137 0.4460 0.2135 -1.250 0.1195 0.01170 0.00400 -0.0130 0.4420 0.2442 -1.000 0.1432 0.01149 0.00396 -0.0122 0.4379 0.2883 -0.750 0.1661 0.01129 0.00393 -0.0112 0.4338 0.3381 -0.500 0.1884 0.01116 0.00391 -0.0101 0.4297 0.3891 -0.250 0.2089 0.01088 0.00390 -0.0087 0.4265 0.4564 0.000 0.2243 0.01043 0.00390 -0.0062 0.4234 0.5681 0.250 0.2390 0.01005 0.00390 -0.0034 0.4201 0.6674 0.500 0.2563 0.00976 0.00399 -0.0009 0.4166 0.7722 0.750 0.2862 0.00977 0.00415 -0.0009 0.4126 0.8369 1.000 0.3249 0.00993 0.00437 -0.0028 0.4086 0.8762 1.250 0.3671 0.01009 0.00456 -0.0055 0.4049 0.8979 1.500 0.4015 0.01027 0.00473 -0.0065 0.4013 0.9139 1.750 0.4464 0.01054 0.00494 -0.0098 0.3975 0.9223 2.000 0.4756 0.01081 0.00513 -0.0098 0.3940 0.9324 2.250 0.5201 0.01113 0.00541 -0.0130 0.3904 0.9363 2.500 0.5591 0.01138 0.00565 -0.0151 0.3872 0.9417 2.750 0.5954 0.01166 0.00591 -0.0165 0.3837 0.9495 3.000 0.6494 0.01203 0.00622 -0.0215 0.3798 0.9534 3.250 0.6916 0.01240 0.00650 -0.0243 0.3762 0.9597 3.500 0.7267 0.01269 0.00675 -0.0257 0.3731 0.9650 3.750 0.7690 0.01283 0.00689 -0.0287 0.3704 0.9671 4.000 0.8118 0.01300 0.00706 -0.0317 0.3672 0.9705 4.250 0.8483 0.01320 0.00724 -0.0336 0.3642 0.9756 4.500 0.8833 0.01337 0.00736 -0.0352 0.3611 0.9794 4.750 0.9202 0.01356 0.00747 -0.0373 0.3576 0.9812 5.000 0.9558 0.01369 0.00761 -0.0391 0.3551 0.9834 5.250 0.9904 0.01379 0.00773 -0.0407 0.3527 0.9862 5.500 1.0246 0.01391 0.00786 -0.0423 0.3499 0.9898 5.750 1.0613 0.01402 0.00796 -0.0444 0.3470 0.9928 6.000 1.0992 0.01410 0.00801 -0.0468 0.3441 0.9953 6.250 1.1335 0.01428 0.00814 -0.0485 0.3411 0.9978 6.500 1.1666 0.01448 0.00832 -0.0500 0.3384 0.9997 6.750 1.1885 0.01460 0.00849 -0.0493 0.3362 1.0000 7.000 1.2070 0.01475 0.00868 -0.0479 0.3339 1.0000 7.250 1.2250 0.01493 0.00887 -0.0465 0.3314 1.0000 7.500 1.2424 0.01512 0.00906 -0.0449 0.3290 1.0000 7.750 1.2590 0.01535 0.00928 -0.0433 0.3267 1.0000 8.000 1.2749 0.01566 0.00954 -0.0415 0.3239 1.0000 8.250 1.2910 0.01596 0.00985 -0.0398 0.3218 1.0000 8.500 1.3051 0.01618 0.01013 -0.0377 0.3201 1.0000 8.750 1.3182 0.01642 0.01042 -0.0355 0.3181 1.0000 9.000 1.3298 0.01667 0.01070 -0.0330 0.3159 1.0000 9.250 1.3395 0.01693 0.01099 -0.0302 0.3137 1.0000 9.500 1.3442 0.01720 0.01127 -0.0265 0.3117 1.0000 9.750 1.3449 0.01750 0.01157 -0.0222 0.3098 1.0000 10.000 1.3510 0.01790 0.01194 -0.0190 0.3076 1.0000 10.250 1.3596 0.01832 0.01237 -0.0163 0.3055 1.0000 10.500 1.3630 0.01878 0.01290 -0.0131 0.3039 1.0000 10.750 1.3688 0.01929 0.01348 -0.0104 0.3020 1.0000 11.000 1.3765 0.01985 0.01408 -0.0082 0.2998 1.0000 11.250 1.3854 0.02043 0.01469 -0.0062 0.2976 1.0000 11.500 1.3948 0.02105 0.01533 -0.0044 0.2953 1.0000 11.750 1.4058 0.02168 0.01595 -0.0028 0.2929 1.0000 12.000 1.4226 0.02219 0.01641 -0.0018 0.2901 1.0000 12.250 1.4294 0.02305 0.01736 -0.0001 0.2885 1.0000 12.500 1.4371 0.02393 0.01832 0.0014 0.2865 1.0000 12.750 1.4457 0.02483 0.01928 0.0027 0.2841 1.0000 13.000 1.4550 0.02574 0.02023 0.0038 0.2818 1.0000 13.250 1.4643 0.02667 0.02119 0.0049 0.2794 1.0000 13.500 1.4756 0.02753 0.02203 0.0058 0.2769 1.0000 13.750 1.4911 0.02817 0.02264 0.0066 0.2741 1.0000 14.000 1.4927 0.02970 0.02430 0.0077 0.2719 1.0000 14.250 1.4969 0.03113 0.02582 0.0086 0.2692 1.0000 14.500 1.5029 0.03248 0.02722 0.0094 0.2665 1.0000 14.750 1.5083 0.03391 0.02867 0.0100 0.2635 1.0000 15.000 1.5185 0.03497 0.02970 0.0106 0.2602 1.0000 15.250 1.5202 0.03685 0.03166 0.0112 0.2571 1.0000 15.500 1.5190 0.03908 0.03399 0.0116 0.2537 1.0000 15.750 1.5195 0.04124 0.03621 0.0118 0.2501 1.0000 16.000 1.5236 0.04306 0.03800 0.0121 0.2462 1.0000 16.250 1.5258 0.04511 0.04009 0.0123 0.2427 1.0000 16.500 1.5203 0.04809 0.04320 0.0122 0.2390 1.0000 16.750 1.5189 0.05069 0.04584 0.0122 0.2354 1.0000 17.000 1.5207 0.05290 0.04804 0.0122 0.2316 1.0000 17.250 1.5195 0.05548 0.05066 0.0121 0.2281 1.0000 17.500 1.5125 0.05883 0.05413 0.0117 0.2245 1.0000 17.750 1.5082 0.06188 0.05722 0.0114 0.2204 1.0000 18.000 1.5089 0.06433 0.05967 0.0112 0.2172 1.0000 18.250 1.5062 0.06720 0.06259 0.0109 0.2137 1.0000 18.500 1.4955 0.07117 0.06667 0.0102 0.2100 1.0000 18.750 1.4896 0.07455 0.07008 0.0096 0.2060 1.0000 19.000 1.4915 0.07693 0.07243 0.0093 0.2026 1.0000 19.250 1.4813 0.08091 0.07651 0.0085 0.1990 1.0000