XFOIL Version 6.96 Calculated polar for: GIII BL387 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.500 -0.6639 0.17247 0.17068 0.0381 1.0000 0.0076 -14.250 -0.6574 0.16918 0.16740 0.0366 1.0000 0.0077 -8.750 -0.8020 0.01990 0.01571 -0.0236 1.0000 0.0115 -8.500 -0.7837 0.01789 0.01339 -0.0224 1.0000 0.0117 -8.250 -0.7626 0.01672 0.01205 -0.0214 1.0000 0.0119 -8.000 -0.7409 0.01585 0.01103 -0.0204 1.0000 0.0120 -7.750 -0.7190 0.01511 0.01018 -0.0194 1.0000 0.0121 -7.500 -0.6948 0.01413 0.00907 -0.0190 0.9990 0.0124 -7.250 -0.6636 0.01346 0.00833 -0.0199 0.9960 0.0127 -7.000 -0.6317 0.01296 0.00778 -0.0210 0.9923 0.0129 -6.750 -0.5992 0.01253 0.00731 -0.0221 0.9869 0.0132 -6.500 -0.5676 0.01210 0.00683 -0.0230 0.9800 0.0135 -6.250 -0.5360 0.01168 0.00637 -0.0239 0.9719 0.0138 -6.000 -0.5054 0.01126 0.00589 -0.0245 0.9611 0.0141 -5.750 -0.4772 0.01088 0.00543 -0.0246 0.9460 0.0145 -5.500 -0.4509 0.01054 0.00501 -0.0241 0.9291 0.0148 -5.250 -0.4250 0.01025 0.00464 -0.0236 0.9141 0.0151 -5.000 -0.3993 0.00991 0.00423 -0.0231 0.9010 0.0156 -4.750 -0.3729 0.00970 0.00399 -0.0227 0.8874 0.0161 -4.500 -0.3463 0.00953 0.00378 -0.0223 0.8737 0.0166 -4.250 -0.3197 0.00935 0.00355 -0.0220 0.8606 0.0171 -4.000 -0.2929 0.00917 0.00331 -0.0217 0.8484 0.0178 -3.750 -0.2661 0.00899 0.00307 -0.0214 0.8363 0.0183 -3.500 -0.2393 0.00882 0.00285 -0.0211 0.8240 0.0189 -3.250 -0.2124 0.00866 0.00267 -0.0208 0.8113 0.0198 -3.000 -0.1852 0.00856 0.00254 -0.0206 0.7990 0.0206 -2.750 -0.1580 0.00843 0.00237 -0.0203 0.7875 0.0215 -2.500 -0.1308 0.00831 0.00220 -0.0201 0.7760 0.0222 -2.250 -0.1033 0.00822 0.00208 -0.0199 0.7644 0.0229 -2.000 -0.0763 0.00804 0.00187 -0.0197 0.7522 0.0241 -1.750 -0.0490 0.00794 0.00174 -0.0194 0.7394 0.0251 -1.500 -0.0217 0.00787 0.00162 -0.0192 0.7243 0.0261 -1.250 0.0054 0.00782 0.00151 -0.0190 0.7028 0.0272 -1.000 0.0323 0.00782 0.00142 -0.0187 0.6748 0.0281 -0.750 0.0590 0.00780 0.00129 -0.0183 0.6408 0.0294 -0.500 0.0856 0.00782 0.00120 -0.0180 0.6045 0.0311 -0.250 0.1125 0.00787 0.00115 -0.0178 0.5723 0.0328 0.000 0.1396 0.00792 0.00111 -0.0176 0.5433 0.0347 0.250 0.1667 0.00795 0.00107 -0.0174 0.5186 0.0380 0.500 0.1940 0.00798 0.00105 -0.0172 0.4970 0.0427 0.750 0.2211 0.00802 0.00104 -0.0170 0.4740 0.0524 1.000 0.2423 0.00687 0.00097 -0.0164 0.4507 0.4733 1.250 0.2633 0.00615 0.00099 -0.0152 0.4307 0.7273 1.500 0.2887 0.00609 0.00105 -0.0146 0.4110 0.7864 1.750 0.3145 0.00615 0.00110 -0.0141 0.3814 0.8195 2.000 0.3399 0.00627 0.00118 -0.0135 0.3410 0.8492 2.250 0.3638 0.00638 0.00129 -0.0125 0.3060 0.8926 2.500 0.3879 0.00654 0.00142 -0.0115 0.2697 0.9362 2.750 0.4159 0.00679 0.00155 -0.0115 0.2343 0.9544 3.000 0.4451 0.00705 0.00167 -0.0119 0.2022 0.9644 3.250 0.4752 0.00736 0.00182 -0.0125 0.1673 0.9724 3.500 0.5065 0.00762 0.00196 -0.0133 0.1424 0.9786 3.750 0.5371 0.00787 0.00210 -0.0141 0.1203 0.9848 4.000 0.5692 0.00812 0.00225 -0.0151 0.1031 0.9889 4.250 0.6004 0.00833 0.00241 -0.0160 0.0913 0.9931 4.500 0.6324 0.00855 0.00257 -0.0170 0.0817 0.9963 5.000 0.6910 0.00898 0.00292 -0.0179 0.0665 1.0000 5.250 0.7155 0.00921 0.00310 -0.0172 0.0604 1.0000 5.500 0.7403 0.00940 0.00328 -0.0166 0.0564 1.0000 5.750 0.7650 0.00965 0.00348 -0.0161 0.0516 1.0000 6.000 0.7903 0.00985 0.00369 -0.0156 0.0488 1.0000 6.250 0.8154 0.01009 0.00390 -0.0151 0.0451 1.0000 6.500 0.8405 0.01035 0.00415 -0.0147 0.0416 1.0000 6.750 0.8660 0.01058 0.00439 -0.0143 0.0393 1.0000 7.000 0.8912 0.01086 0.00464 -0.0139 0.0363 1.0000 7.250 0.9164 0.01115 0.00492 -0.0135 0.0341 1.0000 7.500 0.9419 0.01140 0.00520 -0.0131 0.0329 1.0000 7.750 0.9673 0.01167 0.00548 -0.0128 0.0314 1.0000 8.000 0.9924 0.01198 0.00578 -0.0124 0.0297 1.0000 8.250 1.0172 0.01235 0.00615 -0.0120 0.0280 1.0000 8.500 1.0424 0.01263 0.00647 -0.0117 0.0273 1.0000 8.750 1.0675 0.01293 0.00680 -0.0114 0.0263 1.0000 9.000 1.0924 0.01326 0.00715 -0.0110 0.0252 1.0000 9.250 1.1169 0.01362 0.00753 -0.0106 0.0241 1.0000 9.500 1.1409 0.01405 0.00797 -0.0102 0.0228 1.0000 9.750 1.1654 0.01441 0.00837 -0.0098 0.0221 1.0000 10.000 1.1897 0.01478 0.00877 -0.0094 0.0213 1.0000 10.250 1.2137 0.01517 0.00921 -0.0090 0.0203 1.0000 10.500 1.2373 0.01561 0.00966 -0.0086 0.0193 1.0000 10.750 1.2601 0.01613 0.01019 -0.0081 0.0182 1.0000 11.000 1.2834 0.01655 0.01068 -0.0076 0.0176 1.0000 11.250 1.3063 0.01702 0.01120 -0.0071 0.0169 1.0000 11.500 1.3286 0.01753 0.01174 -0.0065 0.0162 1.0000 11.750 1.3504 0.01808 0.01232 -0.0059 0.0155 1.0000 12.000 1.3713 0.01870 0.01299 -0.0052 0.0149 1.0000 12.250 1.3919 0.01933 0.01368 -0.0045 0.0144 1.0000 12.500 1.4125 0.01991 0.01433 -0.0038 0.0140 1.0000 12.750 1.4323 0.02054 0.01502 -0.0030 0.0136 1.0000 13.000 1.4513 0.02121 0.01576 -0.0021 0.0132 1.0000 13.250 1.4693 0.02193 0.01655 -0.0012 0.0128 1.0000 13.500 1.4862 0.02271 0.01739 -0.0001 0.0125 1.0000 13.750 1.5016 0.02356 0.01831 0.0011 0.0122 1.0000 14.000 1.5133 0.02451 0.01934 0.0028 0.0119 1.0000 14.250 1.5222 0.02559 0.02050 0.0047 0.0116 1.0000 14.500 1.5325 0.02657 0.02157 0.0063 0.0114 1.0000 14.750 1.5413 0.02769 0.02279 0.0078 0.0112 1.0000 15.000 1.5487 0.02898 0.02418 0.0092 0.0111 1.0000 15.250 1.5548 0.03047 0.02578 0.0103 0.0109 1.0000 15.500 1.5595 0.03219 0.02759 0.0112 0.0108 1.0000 15.750 1.5629 0.03415 0.02967 0.0118 0.0106 1.0000 16.000 1.5649 0.03640 0.03203 0.0121 0.0105 1.0000 16.250 1.5651 0.03901 0.03475 0.0119 0.0103 1.0000 16.500 1.5633 0.04202 0.03788 0.0114 0.0102 1.0000 16.750 1.5591 0.04553 0.04151 0.0104 0.0101 1.0000 17.000 1.5522 0.04964 0.04575 0.0088 0.0100 1.0000 17.250 1.5419 0.05449 0.05073 0.0066 0.0099 1.0000 17.500 1.5277 0.06015 0.05654 0.0038 0.0099 1.0000 17.750 1.5087 0.06678 0.06332 0.0004 0.0098 1.0000 18.000 1.4836 0.07453 0.07123 -0.0036 0.0098 1.0000 18.250 1.4517 0.08378 0.08065 -0.0085 0.0098 1.0000 18.500 1.4122 0.09474 0.09180 -0.0143 0.0099 1.0000 18.750 1.3645 0.10763 0.10489 -0.0210 0.0100 1.0000 19.000 1.3127 0.12171 0.11915 -0.0285 0.0102 1.0000