XFOIL Version 6.96 Calculated polar for: GOE 766 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.5608 0.09468 0.09080 -0.0086 1.0000 0.0948 -10.000 -0.8562 0.04950 0.04410 -0.0259 1.0000 0.0588 -9.750 -0.8535 0.04550 0.03992 -0.0241 1.0000 0.0584 -9.500 -0.8529 0.04205 0.03615 -0.0216 1.0000 0.0583 -9.250 -0.8499 0.03915 0.03287 -0.0188 1.0000 0.0585 -9.000 -0.8445 0.03644 0.02977 -0.0161 1.0000 0.0591 -8.750 -0.8327 0.03348 0.02661 -0.0143 1.0000 0.0596 -8.500 -0.8173 0.03136 0.02433 -0.0126 1.0000 0.0602 -8.250 -0.8000 0.02966 0.02250 -0.0111 1.0000 0.0609 -8.000 -0.7811 0.02830 0.02105 -0.0096 1.0000 0.0619 -7.750 -0.7624 0.02707 0.01970 -0.0081 1.0000 0.0632 -7.500 -0.7436 0.02575 0.01819 -0.0064 1.0000 0.0645 -7.250 -0.7242 0.02446 0.01669 -0.0048 1.0000 0.0656 -7.000 -0.7039 0.02332 0.01536 -0.0032 1.0000 0.0665 -6.750 -0.6833 0.02240 0.01426 -0.0016 1.0000 0.0675 -6.500 -0.6614 0.02087 0.01278 -0.0006 1.0000 0.0695 -6.250 -0.6401 0.02008 0.01201 0.0007 1.0000 0.0714 -6.000 -0.6189 0.01932 0.01122 0.0021 1.0000 0.0734 -5.750 -0.5976 0.01859 0.01044 0.0036 1.0000 0.0753 -5.500 -0.5767 0.01798 0.00976 0.0051 1.0000 0.0771 -5.250 -0.5575 0.01700 0.00890 0.0067 1.0000 0.0802 -5.000 -0.5380 0.01648 0.00843 0.0084 1.0000 0.0837 -4.750 -0.5184 0.01601 0.00792 0.0101 1.0000 0.0873 -4.500 -0.5011 0.01532 0.00734 0.0121 1.0000 0.0915 -4.250 -0.4828 0.01492 0.00699 0.0139 1.0000 0.0972 -4.000 -0.4657 0.01446 0.00662 0.0159 1.0000 0.1046 -3.750 -0.4336 0.01400 0.00628 0.0148 0.9958 0.1191 -3.500 -0.3856 0.01332 0.00582 0.0107 0.9849 0.1564 -3.250 -0.3401 0.01254 0.00535 0.0069 0.9720 0.2060 -3.000 -0.2952 0.01170 0.00491 0.0034 0.9563 0.2731 -2.750 -0.2576 0.01060 0.00454 0.0014 0.9341 0.4221 -2.500 -0.2234 0.00971 0.00437 0.0006 0.9053 0.5847 -2.250 -0.1901 0.00934 0.00426 0.0006 0.8623 0.6772 -2.000 -0.1600 0.00921 0.00416 0.0015 0.8053 0.7344 -1.750 -0.1346 0.00928 0.00412 0.0033 0.7471 0.7843 -1.500 -0.1089 0.00950 0.00420 0.0050 0.6994 0.8250 -1.250 -0.0821 0.00976 0.00428 0.0062 0.6616 0.8555 -1.000 -0.0508 0.01003 0.00437 0.0063 0.6305 0.8763 -0.750 -0.0181 0.01031 0.00446 0.0060 0.6049 0.8937 -0.500 0.0171 0.01061 0.00459 0.0053 0.5823 0.9095 -0.250 0.0556 0.01096 0.00479 0.0039 0.5608 0.9247 0.000 0.1030 0.01136 0.00501 0.0006 0.5400 0.9351 0.250 0.1485 0.01167 0.00517 -0.0025 0.5216 0.9439 0.500 0.1872 0.01193 0.00529 -0.0043 0.5052 0.9550 0.750 0.2374 0.01218 0.00540 -0.0085 0.4873 0.9620 1.000 0.2800 0.01238 0.00547 -0.0114 0.4707 0.9715 1.250 0.3230 0.01251 0.00548 -0.0144 0.4548 0.9793 1.500 0.3672 0.01260 0.00545 -0.0178 0.4394 0.9865 1.750 0.4132 0.01268 0.00539 -0.0215 0.4241 0.9946 2.000 0.4535 0.01263 0.00529 -0.0243 0.4092 1.0000 2.250 0.4731 0.01268 0.00531 -0.0230 0.3978 1.0000 2.500 0.4931 0.01281 0.00533 -0.0217 0.3885 1.0000 2.750 0.5135 0.01287 0.00539 -0.0204 0.3781 1.0000 3.000 0.5343 0.01301 0.00546 -0.0192 0.3693 1.0000 3.250 0.5553 0.01310 0.00554 -0.0179 0.3600 1.0000 3.500 0.5765 0.01328 0.00566 -0.0167 0.3519 1.0000 3.750 0.5977 0.01339 0.00577 -0.0155 0.3431 1.0000 4.000 0.6191 0.01359 0.00592 -0.0142 0.3353 1.0000 4.250 0.6406 0.01373 0.00607 -0.0130 0.3271 1.0000 4.500 0.6622 0.01398 0.00624 -0.0118 0.3201 1.0000 4.750 0.6838 0.01414 0.00645 -0.0106 0.3121 1.0000 5.000 0.7055 0.01439 0.00661 -0.0094 0.3047 1.0000 5.250 0.7270 0.01452 0.00682 -0.0081 0.2959 1.0000 5.500 0.7487 0.01481 0.00700 -0.0069 0.2885 1.0000 5.750 0.7704 0.01497 0.00727 -0.0057 0.2803 1.0000 6.000 0.7921 0.01528 0.00747 -0.0045 0.2731 1.0000 6.250 0.8137 0.01547 0.00778 -0.0033 0.2649 1.0000 6.500 0.8353 0.01577 0.00801 -0.0021 0.2573 1.0000 6.750 0.8567 0.01598 0.00833 -0.0009 0.2486 1.0000 7.000 0.8779 0.01633 0.00857 0.0004 0.2403 1.0000 7.250 0.8990 0.01647 0.00887 0.0017 0.2304 1.0000 7.500 0.9197 0.01677 0.00916 0.0030 0.2208 1.0000 7.750 0.9401 0.01702 0.00941 0.0043 0.2100 1.0000 8.000 0.9605 0.01724 0.00973 0.0056 0.1974 1.0000 8.250 0.9804 0.01754 0.01006 0.0070 0.1834 1.0000 8.500 0.9994 0.01792 0.01042 0.0085 0.1680 1.0000 8.750 1.0172 0.01844 0.01088 0.0101 0.1525 1.0000 9.000 1.0335 0.01912 0.01149 0.0119 0.1387 1.0000 9.250 1.0493 0.01988 0.01223 0.0137 0.1273 1.0000 9.500 1.0642 0.02072 0.01306 0.0156 0.1184 1.0000 9.750 1.0767 0.02175 0.01397 0.0177 0.1115 1.0000 10.000 1.0925 0.02251 0.01484 0.0195 0.1056 1.0000 10.250 1.1052 0.02352 0.01578 0.0215 0.1009 1.0000 10.500 1.1189 0.02449 0.01682 0.0234 0.0968 1.0000 10.750 1.1325 0.02535 0.01773 0.0253 0.0930 1.0000 11.000 1.1445 0.02643 0.01877 0.0272 0.0897 1.0000 11.250 1.1569 0.02761 0.02001 0.0290 0.0870 1.0000 11.500 1.1683 0.02860 0.02112 0.0310 0.0845 1.0000 11.750 1.1776 0.02960 0.02216 0.0333 0.0821 1.0000 12.000 1.1871 0.03068 0.02323 0.0353 0.0800 1.0000 12.250 1.2000 0.03228 0.02480 0.0367 0.0777 1.0000 12.500 1.2042 0.03345 0.02615 0.0391 0.0763 1.0000 12.750 1.2091 0.03479 0.02765 0.0411 0.0747 1.0000 13.000 1.2143 0.03620 0.02916 0.0427 0.0731 1.0000 13.250 1.2212 0.03762 0.03063 0.0440 0.0714 1.0000 13.500 1.2327 0.03911 0.03209 0.0448 0.0698 1.0000 13.750 1.2406 0.04132 0.03437 0.0457 0.0684 1.0000 14.000 1.2364 0.04345 0.03673 0.0467 0.0675 1.0000 14.250 1.2319 0.04591 0.03939 0.0471 0.0665 1.0000 14.500 1.2280 0.04857 0.04222 0.0471 0.0655 1.0000 14.750 1.2233 0.05152 0.04533 0.0467 0.0645 1.0000 15.000 1.2196 0.05449 0.04844 0.0459 0.0635 1.0000 15.250 1.2189 0.05727 0.05129 0.0452 0.0625 1.0000 15.500 1.2229 0.05974 0.05378 0.0449 0.0614 1.0000 15.750 1.2274 0.06274 0.05679 0.0450 0.0602 1.0000 16.000 1.2077 0.06783 0.06212 0.0423 0.0599 1.0000 16.250 1.1824 0.07406 0.06859 0.0386 0.0596 1.0000 16.500 1.1555 0.08103 0.07580 0.0345 0.0595 1.0000 16.750 1.1209 0.08971 0.08471 0.0290 0.0595 1.0000 17.000 1.0744 0.10119 0.09644 0.0216 0.0597 1.0000