XFOIL Version 6.96 Calculated polar for: GOE 770 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.750 -0.8142 0.09585 0.09079 -0.0475 1.0000 0.0385 -17.500 -0.8547 0.08514 0.07975 -0.0545 1.0000 0.0387 -17.250 -0.8813 0.07747 0.07179 -0.0592 1.0000 0.0390 -17.000 -0.8912 0.07270 0.06688 -0.0618 1.0000 0.0393 -16.750 -0.8911 0.06952 0.06367 -0.0633 1.0000 0.0396 -16.500 -0.8916 0.06632 0.06041 -0.0647 1.0000 0.0399 -16.250 -0.8928 0.06312 0.05713 -0.0661 1.0000 0.0402 -16.000 -0.8943 0.05997 0.05390 -0.0674 1.0000 0.0405 -15.750 -0.8952 0.05695 0.05078 -0.0685 1.0000 0.0409 -15.500 -0.8952 0.05408 0.04781 -0.0695 1.0000 0.0413 -15.250 -0.8943 0.05137 0.04499 -0.0703 1.0000 0.0418 -15.000 -0.8927 0.04878 0.04227 -0.0710 1.0000 0.0423 -14.750 -0.8902 0.04632 0.03966 -0.0715 1.0000 0.0429 -14.500 -0.8870 0.04400 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0.500 0.3791 0.01471 0.00616 -0.0379 0.4765 0.6347 0.750 0.4069 0.01474 0.00614 -0.0379 0.4729 0.6430 1.000 0.4347 0.01480 0.00621 -0.0379 0.4687 0.6499 1.250 0.4621 0.01483 0.00630 -0.0378 0.4642 0.6566 1.500 0.4896 0.01487 0.00635 -0.0378 0.4599 0.6642 1.750 0.5171 0.01492 0.00638 -0.0377 0.4561 0.6731 2.000 0.5441 0.01497 0.00645 -0.0376 0.4525 0.6834 2.500 0.5975 0.01509 0.00670 -0.0373 0.4429 0.7056 2.750 0.6240 0.01514 0.00676 -0.0370 0.4386 0.7196 3.000 0.6501 0.01521 0.00687 -0.0367 0.4345 0.7361 3.250 0.6757 0.01529 0.00707 -0.0363 0.4295 0.7539 3.500 0.7013 0.01537 0.00722 -0.0360 0.4250 0.7728 3.750 0.7270 0.01546 0.00734 -0.0356 0.4211 0.7924 4.000 0.7526 0.01557 0.00750 -0.0351 0.4173 0.8145 4.250 0.7784 0.01571 0.00776 -0.0348 0.4127 0.8389 4.500 0.8052 0.01586 0.00797 -0.0347 0.4083 0.8651 4.750 0.8339 0.01603 0.00816 -0.0349 0.4044 0.8917 5.000 0.8664 0.01625 0.00837 -0.0360 0.4006 0.9164 5.250 0.9016 0.01651 0.00870 -0.0378 0.3957 0.9396 5.500 0.9369 0.01677 0.00897 -0.0396 0.3912 0.9609 5.750 0.9719 0.01704 0.00920 -0.0415 0.3874 0.9788 6.000 1.0083 0.01734 0.00946 -0.0437 0.3841 0.9924 6.250 1.0400 0.01765 0.00981 -0.0451 0.3803 1.0000 6.500 1.0574 0.01791 0.01009 -0.0435 0.3771 1.0000 6.750 1.0754 0.01819 0.01035 -0.0421 0.3740 1.0000 7.000 1.0943 0.01847 0.01061 -0.0408 0.3712 1.0000 7.250 1.1143 0.01878 0.01086 -0.0398 0.3687 1.0000 7.500 1.1333 0.01912 0.01122 -0.0387 0.3659 1.0000 7.750 1.1515 0.01948 0.01164 -0.0374 0.3627 1.0000 8.000 1.1699 0.01985 0.01204 -0.0363 0.3597 1.0000 8.250 1.1887 0.02023 0.01244 -0.0352 0.3570 1.0000 8.500 1.2081 0.02061 0.01281 -0.0342 0.3546 1.0000 8.750 1.2278 0.02100 0.01317 -0.0333 0.3524 1.0000 9.000 1.2464 0.02142 0.01359 -0.0323 0.3501 1.0000 9.250 1.2588 0.02195 0.01422 -0.0304 0.3471 1.0000 9.500 1.2714 0.02251 0.01484 -0.0287 0.3436 1.0000 9.750 1.2851 0.02307 0.01543 -0.0273 0.3399 1.0000 10.000 1.3015 0.02359 0.01594 -0.0263 0.3367 1.0000 10.250 1.3199 0.02412 0.01642 -0.0255 0.3336 1.0000 10.500 1.3285 0.02502 0.01746 -0.0240 0.3302 1.0000 10.750 1.3392 0.02592 0.01846 -0.0228 0.3270 1.0000 11.000 1.3515 0.02681 0.01941 -0.0219 0.3241 1.0000 11.250 1.3655 0.02765 0.02027 -0.0212 0.3214 1.0000 11.500 1.3825 0.02833 0.02094 -0.0206 0.3187 1.0000 11.750 1.3959 0.02928 0.02193 -0.0200 0.3161 1.0000 12.000 1.4001 0.03083 0.02363 -0.0190 0.3129 1.0000 12.250 1.4054 0.03239 0.02530 -0.0183 0.3094 1.0000 12.500 1.4128 0.03383 0.02680 -0.0177 0.3058 1.0000 12.750 1.4266 0.03477 0.02772 -0.0173 0.3023 1.0000 13.000 1.4315 0.03649 0.02952 -0.0168 0.2987 1.0000 13.250 1.4270 0.03911 0.03230 -0.0163 0.2944 1.0000 13.500 1.4273 0.04133 0.03460 -0.0159 0.2900 1.0000 13.750 1.4377 0.04260 0.03586 -0.0156 0.2860 1.0000 14.000 1.4343 0.04530 0.03867 -0.0154 0.2818 1.0000 14.250 1.4239 0.04879 0.04232 -0.0152 0.2769 1.0000 14.500 1.4250 0.05114 0.04471 -0.0152 0.2723 1.0000 14.750 1.4296 0.05315 0.04673 -0.0151 0.2679 1.0000 15.000 1.4089 0.05812 0.05190 -0.0154 0.2620 1.0000 15.250 1.4083 0.06083 0.05466 -0.0156 0.2567 1.0000 15.500 1.4000 0.06455 0.05846 -0.0159 0.2512 1.0000 15.750 1.3824 0.06950 0.06352 -0.0165 0.2443 1.0000 16.000 1.3808 0.07252 0.06656 -0.0168 0.2383 1.0000 16.250 1.3558 0.07863 0.07281 -0.0178 0.2304 1.0000 16.500 1.3492 0.08242 0.07663 -0.0184 0.2235 1.0000 16.750 1.3323 0.08764 0.08191 -0.0193 0.2151 1.0000 17.000 1.3183 0.09255 0.08687 -0.0203 0.2070 1.0000