XFOIL Version 6.96 Calculated polar for: GIII BL450 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 ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5571 0.08830 0.08599 0.0106 1.0000 0.0149 -8.000 -0.5574 0.08358 0.08129 0.0063 1.0000 0.0149 -7.750 -0.5559 0.07809 0.07578 -0.0002 1.0000 0.0149 -7.500 -0.5499 0.07277 0.07042 -0.0053 1.0000 0.0149 -7.250 -0.5416 0.06760 0.06518 -0.0094 1.0000 0.0152 -7.000 -0.5320 0.06206 0.05954 -0.0130 1.0000 0.0155 -6.750 -0.5209 0.05646 0.05379 -0.0158 1.0000 0.0156 -6.500 -0.5108 0.04895 0.04599 -0.0182 1.0000 0.0160 -6.250 -0.4939 0.04409 0.04092 -0.0193 0.9881 0.0163 -6.000 -0.4648 0.04165 0.03834 -0.0215 0.9508 0.0165 -5.750 -0.4404 0.03926 0.03578 -0.0222 0.9281 0.0168 -5.500 -0.4194 0.03670 0.03301 -0.0220 0.9109 0.0172 -4.500 -0.3355 0.01936 0.01388 -0.0183 0.8644 0.0222 -4.250 -0.3092 0.01926 0.01374 -0.0180 0.8524 0.0224 -4.000 -0.2830 0.01905 0.01348 -0.0176 0.8406 0.0227 -3.500 -0.2331 0.01399 0.00766 -0.0160 0.8186 0.0258 -3.250 -0.2061 0.01392 0.00758 -0.0157 0.8065 0.0262 -3.000 -0.1791 0.01380 0.00741 -0.0153 0.7928 0.0267 -2.750 -0.1523 0.01334 0.00685 -0.0149 0.7774 0.0275 -2.500 -0.1260 0.01248 0.00583 -0.0144 0.7604 0.0286 -2.250 -0.0997 0.01174 0.00491 -0.0138 0.7419 0.0296 -2.000 -0.0727 0.01160 0.00474 -0.0134 0.7196 0.0302 -1.750 -0.0461 0.01153 0.00456 -0.0130 0.6898 0.0309 -1.500 -0.0197 0.01133 0.00421 -0.0125 0.6576 0.0318 -1.250 0.0066 0.01104 0.00377 -0.0120 0.6290 0.0329 -0.750 0.0600 0.01067 0.00320 -0.0112 0.5819 0.0346 -0.500 0.0873 0.01061 0.00310 -0.0109 0.5629 0.0357 -0.250 0.1145 0.01049 0.00290 -0.0106 0.5450 0.0369 0.000 0.1416 0.01035 0.00268 -0.0103 0.5269 0.0381 0.250 0.1687 0.01022 0.00250 -0.0100 0.5097 0.0392 0.500 0.1960 0.01018 0.00242 -0.0098 0.4918 0.0405 0.750 0.2234 0.01015 0.00234 -0.0096 0.4748 0.0422 1.000 0.2509 0.01010 0.00223 -0.0093 0.4599 0.0437 1.250 0.2782 0.01003 0.00213 -0.0091 0.4445 0.0452 1.500 0.3057 0.01001 0.00209 -0.0089 0.4280 0.0471 1.750 0.3332 0.01003 0.00206 -0.0087 0.4093 0.0494 2.000 0.3605 0.01004 0.00201 -0.0085 0.3851 0.0514 2.250 0.3874 0.01016 0.00200 -0.0083 0.3453 0.0538 2.750 0.4400 0.01073 0.00214 -0.0079 0.2442 0.0597 3.000 0.4671 0.01089 0.00223 -0.0077 0.2231 0.0637 3.250 0.4942 0.01104 0.00233 -0.0075 0.2056 0.0699 3.500 0.5214 0.01117 0.00245 -0.0074 0.1914 0.0870 3.750 0.5363 0.00940 0.00261 -0.0053 0.1804 0.8275 4.000 0.5739 0.00934 0.00281 -0.0068 0.1643 0.9797 4.250 0.6128 0.00959 0.00296 -0.0093 0.1491 1.0000 4.500 0.6385 0.00981 0.00311 -0.0088 0.1379 1.0000 4.750 0.6643 0.01006 0.00328 -0.0084 0.1270 1.0000 5.000 0.6900 0.01032 0.00347 -0.0080 0.1168 1.0000 5.250 0.7158 0.01058 0.00367 -0.0076 0.1077 1.0000 5.500 0.7418 0.01083 0.00389 -0.0073 0.0999 1.0000 6.000 0.7936 0.01139 0.00436 -0.0066 0.0863 1.0000 6.250 0.8193 0.01170 0.00462 -0.0062 0.0803 1.0000 6.500 0.8454 0.01197 0.00489 -0.0059 0.0760 1.0000 6.750 0.8710 0.01230 0.00519 -0.0056 0.0715 1.0000 7.000 0.8969 0.01260 0.00549 -0.0053 0.0681 1.0000 7.250 0.9226 0.01292 0.00580 -0.0050 0.0646 1.0000 7.500 0.9479 0.01331 0.00616 -0.0047 0.0614 1.0000 7.750 0.9736 0.01362 0.00650 -0.0044 0.0592 1.0000 8.000 0.9990 0.01396 0.00686 -0.0041 0.0567 1.0000 8.250 1.0240 0.01436 0.00725 -0.0038 0.0541 1.0000 8.500 1.0489 0.01477 0.00768 -0.0034 0.0521 1.0000 8.750 1.0741 0.01514 0.00808 -0.0031 0.0504 1.0000 9.000 1.0989 0.01553 0.00850 -0.0028 0.0483 1.0000 9.250 1.1231 0.01600 0.00897 -0.0024 0.0464 1.0000 9.500 1.1473 0.01647 0.00947 -0.0020 0.0449 1.0000 9.750 1.1716 0.01690 0.00995 -0.0017 0.0435 1.0000 10.000 1.1955 0.01736 0.01045 -0.0013 0.0420 1.0000 10.250 1.2190 0.01787 0.01098 -0.0009 0.0405 1.0000 10.500 1.2415 0.01849 0.01161 -0.0004 0.0391 1.0000 10.750 1.2647 0.01898 0.01218 0.0000 0.0381 1.0000 11.000 1.2873 0.01952 0.01278 0.0005 0.0370 1.0000 11.250 1.3094 0.02010 0.01342 0.0010 0.0359 1.0000 11.500 1.3308 0.02073 0.01409 0.0015 0.0349 1.0000 11.750 1.3508 0.02148 0.01487 0.0021 0.0340 1.0000 12.000 1.3708 0.02220 0.01567 0.0028 0.0331 1.0000 12.250 1.3907 0.02288 0.01643 0.0034 0.0323 1.0000 12.500 1.4097 0.02360 0.01724 0.0041 0.0315 1.0000 12.750 1.4276 0.02438 0.01810 0.0049 0.0307 1.0000 13.000 1.4440 0.02525 0.01903 0.0058 0.0300 1.0000 13.250 1.4580 0.02624 0.02008 0.0068 0.0294 1.0000 13.500 1.4671 0.02743 0.02134 0.0083 0.0288 1.0000 13.750 1.4765 0.02864 0.02265 0.0095 0.0284 1.0000 14.000 1.4853 0.02997 0.02409 0.0104 0.0280 1.0000 14.250 1.4928 0.03150 0.02574 0.0111 0.0276 1.0000 14.500 1.4994 0.03323 0.02759 0.0115 0.0271 1.0000 14.750 1.5048 0.03518 0.02965 0.0117 0.0267 1.0000 15.000 1.5090 0.03740 0.03198 0.0115 0.0263 1.0000 15.250 1.5115 0.03995 0.03464 0.0110 0.0259 1.0000 15.500 1.5119 0.04293 0.03772 0.0100 0.0255 1.0000 15.750 1.5096 0.04639 0.04129 0.0087 0.0252 1.0000 16.000 1.5045 0.05039 0.04541 0.0069 0.0250 1.0000 16.250 1.4961 0.05497 0.05010 0.0048 0.0247 1.0000 16.500 1.4845 0.06009 0.05535 0.0024 0.0245 1.0000 16.750 1.4715 0.06547 0.06085 -0.0001 0.0244 1.0000 17.000 1.4578 0.07107 0.06660 -0.0028 0.0243 1.0000 17.250 1.4415 0.07715 0.07283 -0.0057 0.0242 1.0000 17.500 1.4236 0.08375 0.07957 -0.0090 0.0241 1.0000 17.750 1.4039 0.09084 0.08681 -0.0126 0.0240 1.0000 18.000 1.3830 0.09839 0.09451 -0.0165 0.0239 1.0000 18.250 1.3610 0.10631 0.10256 -0.0206 0.0238 1.0000 18.500 1.3384 0.11450 0.11089 -0.0249 0.0236 1.0000 18.750 1.3162 0.12278 0.11931 -0.0294 0.0235 1.0000 19.000 1.2938 0.13122 0.12787 -0.0340 0.0234 1.0000 19.250 1.2706 0.14010 0.13688 -0.0391 0.0232 1.0000