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 = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5817 0.08325 0.08090 -0.0061 1.0000 0.0142 -8.500 -0.5882 0.07713 0.07480 -0.0129 1.0000 0.0140 -8.250 -0.5918 0.07106 0.06866 -0.0183 1.0000 0.0138 -8.000 -0.5918 0.06515 0.06267 -0.0222 1.0000 0.0137 -7.750 -0.5891 0.05951 0.05690 -0.0247 1.0000 0.0137 -7.500 -0.5836 0.05413 0.05135 -0.0261 1.0000 0.0137 -7.250 -0.5761 0.04897 0.04599 -0.0266 1.0000 0.0138 -7.000 -0.5673 0.04396 0.04075 -0.0263 1.0000 0.0139 -6.750 -0.5581 0.03904 0.03554 -0.0252 1.0000 0.0141 -6.250 -0.5552 0.02019 0.01494 -0.0187 0.9980 0.0154 -6.000 -0.5224 0.01912 0.01373 -0.0202 0.9940 0.0157 -5.750 -0.4897 0.01816 0.01263 -0.0215 0.9886 0.0160 -5.500 -0.4575 0.01701 0.01131 -0.0227 0.9825 0.0164 -5.250 -0.4253 0.01573 0.00983 -0.0237 0.9756 0.0171 -5.000 -0.3943 0.01452 0.00841 -0.0244 0.9661 0.0178 -4.750 -0.3637 0.01356 0.00728 -0.0250 0.9559 0.0185 -4.500 -0.3339 0.01287 0.00652 -0.0254 0.9460 0.0191 -4.250 -0.3050 0.01260 0.00625 -0.0256 0.9356 0.0197 -4.000 -0.2772 0.01231 0.00593 -0.0256 0.9243 0.0205 -3.750 -0.2503 0.01191 0.00546 -0.0252 0.9123 0.0214 -3.500 -0.2241 0.01148 0.00494 -0.0247 0.8997 0.0223 -3.250 -0.1980 0.01114 0.00451 -0.0242 0.8866 0.0230 -3.000 -0.1725 0.01068 0.00403 -0.0236 0.8739 0.0239 -2.750 -0.1460 0.01048 0.00382 -0.0233 0.8615 0.0250 -2.500 -0.1197 0.01027 0.00357 -0.0228 0.8487 0.0263 -2.250 -0.0934 0.01003 0.00327 -0.0223 0.8355 0.0274 -2.000 -0.0671 0.00983 0.00300 -0.0219 0.8225 0.0282 -1.750 -0.0410 0.00951 0.00266 -0.0214 0.8099 0.0297 -1.500 -0.0142 0.00935 0.00248 -0.0211 0.7974 0.0313 -1.250 0.0125 0.00921 0.00230 -0.0207 0.7841 0.0328 -1.000 0.0393 0.00907 0.00211 -0.0204 0.7701 0.0342 -0.750 0.0661 0.00897 0.00195 -0.0200 0.7529 0.0355 -0.500 0.0924 0.00886 0.00178 -0.0195 0.7308 0.0385 -0.250 0.1189 0.00882 0.00166 -0.0191 0.7064 0.0412 0.000 0.1454 0.00881 0.00155 -0.0187 0.6795 0.0439 0.250 0.1718 0.00878 0.00146 -0.0183 0.6497 0.0511 0.500 0.1980 0.00876 0.00139 -0.0179 0.6184 0.0711 0.750 0.2104 0.00671 0.00130 -0.0157 0.5920 0.7211 1.000 0.2334 0.00662 0.00136 -0.0144 0.5635 0.7994 1.250 0.2570 0.00663 0.00142 -0.0132 0.5352 0.8516 1.500 0.2810 0.00672 0.00150 -0.0120 0.5042 0.8935 1.750 0.3078 0.00686 0.00159 -0.0115 0.4757 0.9294 2.000 0.3429 0.00703 0.00170 -0.0127 0.4502 0.9639 2.250 0.3759 0.00721 0.00176 -0.0138 0.4234 0.9746 2.500 0.4089 0.00741 0.00183 -0.0150 0.3914 0.9796 2.750 0.4401 0.00766 0.00191 -0.0159 0.3502 0.9858 3.000 0.4726 0.00804 0.00203 -0.0172 0.2950 0.9901 3.250 0.5042 0.00841 0.00219 -0.0182 0.2503 0.9948 3.500 0.5367 0.00879 0.00237 -0.0195 0.2075 0.9986 3.750 0.5634 0.00914 0.00255 -0.0195 0.1731 1.0000 4.000 0.5870 0.00944 0.00272 -0.0188 0.1485 1.0000 4.250 0.6107 0.00975 0.00292 -0.0181 0.1271 1.0000 4.500 0.6345 0.01004 0.00312 -0.0174 0.1100 1.0000 4.750 0.6585 0.01033 0.00334 -0.0167 0.0969 1.0000 5.000 0.6829 0.01060 0.00357 -0.0161 0.0869 1.0000 5.250 0.7075 0.01085 0.00380 -0.0155 0.0794 1.0000 5.500 0.7320 0.01116 0.00405 -0.0150 0.0719 1.0000 5.750 0.7569 0.01142 0.00430 -0.0144 0.0659 1.0000 6.000 0.7816 0.01174 0.00460 -0.0139 0.0603 1.0000 6.250 0.8066 0.01202 0.00489 -0.0135 0.0563 1.0000 6.500 0.8312 0.01236 0.00521 -0.0130 0.0521 1.0000 6.750 0.8562 0.01268 0.00555 -0.0125 0.0491 1.0000 7.000 0.8810 0.01300 0.00588 -0.0121 0.0460 1.0000 7.250 0.9055 0.01339 0.00626 -0.0116 0.0431 1.0000 7.500 0.9300 0.01376 0.00666 -0.0112 0.0408 1.0000 7.750 0.9548 0.01410 0.00704 -0.0108 0.0386 1.0000 8.000 0.9791 0.01450 0.00744 -0.0103 0.0365 1.0000 8.250 1.0026 0.01500 0.00794 -0.0098 0.0344 1.0000 8.500 1.0268 0.01540 0.00841 -0.0093 0.0334 1.0000 8.750 1.0509 0.01581 0.00888 -0.0089 0.0320 1.0000 9.000 1.0746 0.01625 0.00935 -0.0084 0.0305 1.0000 9.250 1.0978 0.01675 0.00987 -0.0079 0.0290 1.0000 9.500 1.1201 0.01736 0.01052 -0.0073 0.0277 1.0000 9.750 1.1432 0.01784 0.01108 -0.0067 0.0268 1.0000 10.000 1.1658 0.01836 0.01167 -0.0062 0.0257 1.0000 10.250 1.1881 0.01890 0.01228 -0.0056 0.0247 1.0000 10.500 1.2096 0.01951 0.01292 -0.0049 0.0237 1.0000 10.750 1.2293 0.02030 0.01376 -0.0041 0.0227 1.0000 11.000 1.2501 0.02095 0.01450 -0.0033 0.0220 1.0000 11.250 1.2705 0.02161 0.01526 -0.0026 0.0212 1.0000 11.500 1.2903 0.02229 0.01602 -0.0018 0.0204 1.0000 11.750 1.3096 0.02298 0.01679 -0.0010 0.0196 1.0000 12.000 1.3275 0.02378 0.01764 0.0000 0.0189 1.0000 12.250 1.3423 0.02481 0.01874 0.0012 0.0183 1.0000 12.500 1.3573 0.02576 0.01981 0.0024 0.0179 1.0000 12.750 1.3704 0.02673 0.02090 0.0039 0.0175 1.0000 13.000 1.3812 0.02778 0.02207 0.0056 0.0171 1.0000 13.250 1.3906 0.02891 0.02331 0.0072 0.0167 1.0000 13.500 1.3992 0.03015 0.02466 0.0086 0.0163 1.0000 13.750 1.4069 0.03150 0.02611 0.0099 0.0159 1.0000 14.250 1.4174 0.03489 0.02972 0.0116 0.0153 1.0000 14.500 1.4189 0.03715 0.03208 0.0121 0.0150 1.0000 14.750 1.4172 0.03994 0.03499 0.0120 0.0147 1.0000 15.000 1.4136 0.04316 0.03835 0.0115 0.0146 1.0000 15.250 1.4107 0.04654 0.04189 0.0106 0.0144 1.0000 15.500 1.4053 0.05047 0.04598 0.0091 0.0143 1.0000 15.750 1.3976 0.05501 0.05068 0.0071 0.0142 1.0000 16.000 1.3870 0.06019 0.05603 0.0045 0.0141 1.0000 16.250 1.3732 0.06610 0.06210 0.0014 0.0140 1.0000 16.500 1.3559 0.07270 0.06887 -0.0021 0.0140 1.0000 16.750 1.3351 0.08009 0.07642 -0.0061 0.0139 1.0000 17.000 1.3111 0.08831 0.08480 -0.0105 0.0139 1.0000 17.250 1.2842 0.09740 0.09405 -0.0154 0.0139 1.0000 17.500 1.2552 0.10712 0.10392 -0.0206 0.0140 1.0000 17.750 1.2242 0.11755 0.11450 -0.0262 0.0140 1.0000 18.000 1.1920 0.12855 0.12564 -0.0322 0.0141 1.0000 18.250 1.1576 0.14053 0.13776 -0.0388 0.0141 1.0000 18.500 1.1152 0.15516 0.15254 -0.0470 0.0142 1.0000