XFOIL Version 6.96 Calculated polar for: GIII BL369 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.000 -0.5855 0.08557 0.08393 -0.0071 1.0000 0.0164 -8.750 -0.5906 0.07868 0.07705 -0.0155 1.0000 0.0164 -8.500 -0.5946 0.07276 0.07108 -0.0205 1.0000 0.0164 -8.250 -0.5939 0.06696 0.06518 -0.0239 1.0000 0.0165 -8.000 -0.5912 0.06134 0.05945 -0.0261 1.0000 0.0165 -7.750 -0.5996 0.05382 0.05175 -0.0276 1.0000 0.0168 -7.500 -0.5893 0.05098 0.04884 -0.0277 1.0000 0.0170 -7.250 -0.5767 0.04845 0.04623 -0.0276 1.0000 0.0171 -7.000 -0.5634 0.04596 0.04366 -0.0273 1.0000 0.0174 -6.750 -0.5503 0.04343 0.04103 -0.0265 1.0000 0.0177 -6.500 -0.5384 0.04085 0.03834 -0.0252 1.0000 0.0180 -6.250 -0.5280 0.03820 0.03556 -0.0232 1.0000 0.0186 -6.000 -0.5237 0.02183 0.01790 -0.0204 0.9960 0.0162 -5.750 -0.4955 0.01739 0.01283 -0.0210 0.9931 0.0165 -5.500 -0.4671 0.01415 0.00919 -0.0217 0.9896 0.0170 -5.250 -0.4329 0.01350 0.00849 -0.0232 0.9868 0.0174 -5.000 -0.3982 0.01292 0.00786 -0.0248 0.9840 0.0179 -4.750 -0.3682 0.01231 0.00719 -0.0253 0.9771 0.0185 -4.500 -0.3363 0.01166 0.00646 -0.0261 0.9721 0.0193 -4.250 -0.3074 0.01130 0.00604 -0.0262 0.9637 0.0201 -4.000 -0.2799 0.01043 0.00509 -0.0261 0.9553 0.0210 -3.750 -0.2537 0.01001 0.00466 -0.0257 0.9443 0.0218 -3.500 -0.2275 0.00975 0.00439 -0.0253 0.9332 0.0226 -3.250 -0.2014 0.00948 0.00408 -0.0247 0.9223 0.0236 -2.750 -0.1494 0.00895 0.00344 -0.0236 0.8986 0.0255 -2.500 -0.1241 0.00848 0.00296 -0.0231 0.8869 0.0273 -2.250 -0.0975 0.00834 0.00279 -0.0227 0.8752 0.0287 -2.000 -0.0710 0.00816 0.00257 -0.0223 0.8630 0.0300 -1.750 -0.0442 0.00804 0.00240 -0.0219 0.8494 0.0310 -1.500 -0.0184 0.00769 0.00198 -0.0214 0.8346 0.0329 -1.250 0.0083 0.00753 0.00179 -0.0210 0.8198 0.0348 -1.000 0.0352 0.00742 0.00163 -0.0207 0.8053 0.0364 -0.750 0.0623 0.00733 0.00151 -0.0204 0.7903 0.0381 -0.500 0.0893 0.00724 0.00136 -0.0201 0.7745 0.0399 -0.250 0.1161 0.00714 0.00120 -0.0197 0.7567 0.0440 0.000 0.1431 0.00711 0.00111 -0.0194 0.7368 0.0485 0.250 0.1616 0.00550 0.00091 -0.0184 0.7189 0.5353 0.500 0.1802 0.00473 0.00095 -0.0164 0.7013 0.7907 0.750 0.2046 0.00465 0.00097 -0.0154 0.6813 0.8444 1.000 0.2294 0.00466 0.00099 -0.0145 0.6535 0.8791 1.250 0.2536 0.00475 0.00103 -0.0134 0.6145 0.9088 1.500 0.2782 0.00488 0.00109 -0.0124 0.5763 0.9368 1.750 0.3050 0.00505 0.00115 -0.0120 0.5436 0.9576 2.000 0.3346 0.00523 0.00122 -0.0123 0.5125 0.9710 2.250 0.3700 0.00541 0.00131 -0.0138 0.4864 0.9818 2.500 0.4048 0.00561 0.00138 -0.0154 0.4569 0.9863 2.750 0.4397 0.00585 0.00146 -0.0171 0.4163 0.9894 3.000 0.4734 0.00612 0.00154 -0.0185 0.3700 0.9933 3.250 0.5076 0.00646 0.00166 -0.0202 0.3153 0.9959 3.500 0.5419 0.00684 0.00180 -0.0219 0.2619 0.9985 3.750 0.5724 0.00723 0.00197 -0.0228 0.2123 1.0000 4.000 0.5952 0.00757 0.00213 -0.0219 0.1763 1.0000 4.250 0.6182 0.00788 0.00231 -0.0211 0.1468 1.0000 4.500 0.6413 0.00819 0.00249 -0.0203 0.1200 1.0000 4.750 0.6648 0.00848 0.00268 -0.0195 0.1001 1.0000 5.000 0.6886 0.00876 0.00289 -0.0188 0.0860 1.0000 5.250 0.7126 0.00902 0.00310 -0.0181 0.0749 1.0000 5.500 0.7365 0.00931 0.00333 -0.0174 0.0648 1.0000 5.750 0.7603 0.00964 0.00360 -0.0166 0.0555 1.0000 6.000 0.7851 0.00987 0.00383 -0.0161 0.0513 1.0000 6.250 0.8091 0.01025 0.00417 -0.0154 0.0456 1.0000 6.500 0.8344 0.01046 0.00440 -0.0150 0.0436 1.0000 6.750 0.8593 0.01075 0.00469 -0.0145 0.0410 1.0000 7.000 0.8834 0.01118 0.00511 -0.0139 0.0379 1.0000 7.250 0.9084 0.01146 0.00543 -0.0135 0.0366 1.0000 7.500 0.9337 0.01174 0.00573 -0.0131 0.0353 1.0000 7.750 0.9587 0.01205 0.00607 -0.0127 0.0339 1.0000 8.000 0.9832 0.01244 0.00646 -0.0123 0.0322 1.0000 8.250 1.0059 0.01307 0.00713 -0.0116 0.0302 1.0000 8.500 1.0314 0.01330 0.00740 -0.0113 0.0294 1.0000 8.750 1.0563 0.01361 0.00774 -0.0110 0.0281 1.0000 9.000 1.0809 0.01396 0.00811 -0.0106 0.0269 1.0000 9.250 1.1039 0.01452 0.00867 -0.0100 0.0253 1.0000 9.500 1.1265 0.01513 0.00935 -0.0094 0.0241 1.0000 9.750 1.1510 0.01546 0.00973 -0.0090 0.0232 1.0000 10.000 1.1752 0.01582 0.01012 -0.0086 0.0221 1.0000 10.250 1.1988 0.01624 0.01055 -0.0082 0.0210 1.0000 10.500 1.2179 0.01721 0.01158 -0.0072 0.0196 1.0000 10.750 1.2415 0.01760 0.01202 -0.0068 0.0191 1.0000 11.000 1.2641 0.01808 0.01257 -0.0062 0.0184 1.0000 11.250 1.2862 0.01860 0.01314 -0.0056 0.0177 1.0000 11.500 1.3078 0.01915 0.01373 -0.0050 0.0171 1.0000 11.750 1.3275 0.01988 0.01450 -0.0042 0.0164 1.0000 12.000 1.3416 0.02117 0.01588 -0.0027 0.0157 1.0000 12.250 1.3623 0.02171 0.01650 -0.0020 0.0154 1.0000 12.500 1.3811 0.02240 0.01728 -0.0011 0.0150 1.0000 12.750 1.3984 0.02318 0.01815 -0.0001 0.0146 1.0000 13.000 1.4147 0.02399 0.01904 0.0011 0.0142 1.0000 13.250 1.4292 0.02483 0.01995 0.0024 0.0138 1.0000 13.500 1.4408 0.02575 0.02094 0.0041 0.0135 1.0000 13.750 1.4489 0.02690 0.02217 0.0060 0.0132 1.0000 14.000 1.4518 0.02847 0.02384 0.0081 0.0129 1.0000 14.250 1.4466 0.03085 0.02636 0.0102 0.0126 1.0000 14.500 1.4462 0.03303 0.02869 0.0114 0.0124 1.0000 14.750 1.4523 0.03476 0.03053 0.0120 0.0123 1.0000 15.000 1.4559 0.03684 0.03274 0.0123 0.0121 1.0000 15.250 1.4578 0.03928 0.03530 0.0122 0.0119 1.0000 15.500 1.4568 0.04222 0.03837 0.0117 0.0118 1.0000 15.750 1.4529 0.04572 0.04201 0.0107 0.0116 1.0000 16.000 1.4466 0.04978 0.04620 0.0092 0.0115 1.0000 16.250 1.4377 0.05449 0.05106 0.0070 0.0114 1.0000 16.500 1.4255 0.05996 0.05668 0.0043 0.0113 1.0000 16.750 1.4093 0.06630 0.06317 0.0009 0.0113 1.0000 17.000 1.3890 0.07347 0.07048 -0.0029 0.0112 1.0000 17.250 1.3644 0.08162 0.07879 -0.0073 0.0112 1.0000 17.500 1.3355 0.09081 0.08814 -0.0122 0.0113 1.0000 17.750 1.3033 0.10094 0.09842 -0.0177 0.0113 1.0000 18.000 1.2681 0.11191 0.10955 -0.0235 0.0114 1.0000