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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5524 0.09969 0.09737 0.0139 1.0000 0.0245 -8.500 -0.5573 0.09392 0.09162 0.0064 1.0000 0.0246 -8.250 -0.5588 0.08819 0.08591 -0.0006 1.0000 0.0246 -8.000 -0.5509 0.08542 0.08316 0.0013 1.0000 0.0248 -7.750 -0.5431 0.08221 0.07996 0.0004 1.0000 0.0249 -7.500 -0.5349 0.07861 0.07636 -0.0019 1.0000 0.0251 -7.250 -0.5257 0.07481 0.07254 -0.0047 1.0000 0.0254 -7.000 -0.5152 0.07093 0.06862 -0.0076 1.0000 0.0257 -6.750 -0.5031 0.06701 0.06465 -0.0104 1.0000 0.0262 -6.500 -0.4892 0.06303 0.06060 -0.0129 1.0000 0.0269 -6.250 -0.4684 0.05579 0.05286 -0.0182 1.0000 0.0284 -6.000 -0.4553 0.05218 0.04928 -0.0185 1.0000 0.0286 -5.750 -0.4389 0.04956 0.04666 -0.0188 1.0000 0.0288 -5.500 -0.4209 0.04709 0.04416 -0.0191 1.0000 0.0291 -5.250 -0.4017 0.04464 0.04164 -0.0194 1.0000 0.0297 -5.000 -0.3752 0.04166 0.03823 -0.0189 1.0000 0.0325 -4.750 -0.3520 0.03749 0.03391 -0.0202 0.9913 0.0329 -4.500 -0.3221 0.03499 0.03138 -0.0225 0.9768 0.0332 -4.250 -0.2915 0.03288 0.02919 -0.0243 0.9615 0.0339 -4.000 -0.2628 0.03090 0.02705 -0.0250 0.9453 0.0353 -3.750 -0.2352 0.02791 0.02352 -0.0236 0.9298 0.0377 -3.500 -0.2131 0.02629 0.02185 -0.0231 0.9157 0.0382 -3.250 -0.1903 0.02508 0.02056 -0.0225 0.9025 0.0391 -3.000 -0.1614 0.02511 0.02003 -0.0205 0.8899 0.0429 -2.750 -0.1400 0.02190 0.01680 -0.0202 0.8773 0.0437 -2.500 -0.1156 0.02069 0.01555 -0.0197 0.8640 0.0445 -2.250 -0.0902 0.01970 0.01445 -0.0191 0.8509 0.0461 -2.000 -0.0631 0.01858 0.01294 -0.0179 0.8369 0.0501 -1.750 -0.0382 0.01747 0.01181 -0.0174 0.8196 0.0513 -1.500 -0.0122 0.01671 0.01093 -0.0168 0.7998 0.0536 -1.250 0.0161 0.01514 0.00896 -0.0153 0.7796 0.0485 -1.000 0.0425 0.01387 0.00754 -0.0146 0.7566 0.0476 -0.750 0.0693 0.01284 0.00635 -0.0139 0.7305 0.0468 -0.500 0.0959 0.01214 0.00548 -0.0132 0.7026 0.0471 -0.250 0.1227 0.01178 0.00494 -0.0126 0.6728 0.0484 0.000 0.1493 0.01143 0.00442 -0.0120 0.6458 0.0496 0.250 0.1752 0.01086 0.00381 -0.0115 0.6208 0.0508 0.500 0.2018 0.01063 0.00352 -0.0110 0.5981 0.0523 0.750 0.2287 0.01047 0.00331 -0.0107 0.5782 0.0545 1.000 0.2558 0.01037 0.00312 -0.0103 0.5599 0.0563 1.250 0.2822 0.01004 0.00276 -0.0099 0.5434 0.0581 1.500 0.3092 0.00989 0.00259 -0.0096 0.5274 0.0606 1.750 0.3365 0.00984 0.00250 -0.0093 0.5110 0.0637 2.000 0.3638 0.00979 0.00239 -0.0090 0.4943 0.0660 2.250 0.3909 0.00967 0.00224 -0.0087 0.4755 0.0700 2.500 0.4183 0.00967 0.00221 -0.0085 0.4553 0.0747 2.750 0.4456 0.00967 0.00215 -0.0083 0.4330 0.0803 3.000 0.4728 0.00974 0.00215 -0.0080 0.4065 0.0897 3.250 0.4888 0.00798 0.00219 -0.0063 0.3777 0.7913 3.500 0.5407 0.00804 0.00236 -0.0109 0.2980 1.0000 3.750 0.5649 0.00848 0.00254 -0.0103 0.2536 1.0000 4.000 0.5896 0.00884 0.00273 -0.0098 0.2284 1.0000 4.250 0.6149 0.00913 0.00291 -0.0093 0.2094 1.0000 4.500 0.6404 0.00940 0.00310 -0.0088 0.1921 1.0000 4.750 0.6660 0.00968 0.00329 -0.0084 0.1762 1.0000 5.000 0.6917 0.00997 0.00349 -0.0080 0.1608 1.0000 5.250 0.7173 0.01027 0.00370 -0.0076 0.1463 1.0000 5.500 0.7429 0.01059 0.00395 -0.0072 0.1331 1.0000 5.750 0.7685 0.01094 0.00421 -0.0068 0.1211 1.0000 6.000 0.7943 0.01124 0.00448 -0.0065 0.1116 1.0000 6.250 0.8199 0.01160 0.00481 -0.0061 0.1033 1.0000 6.500 0.8451 0.01201 0.00515 -0.0057 0.0955 1.0000 6.750 0.8710 0.01233 0.00547 -0.0054 0.0900 1.0000 7.000 0.8961 0.01276 0.00586 -0.0050 0.0845 1.0000 7.250 0.9214 0.01315 0.00627 -0.0046 0.0803 1.0000 7.500 0.9469 0.01350 0.00661 -0.0043 0.0763 1.0000 7.750 0.9708 0.01412 0.00720 -0.0039 0.0721 1.0000 8.000 0.9964 0.01444 0.00757 -0.0035 0.0696 1.0000 8.250 1.0214 0.01484 0.00798 -0.0032 0.0666 1.0000 8.500 1.0442 0.01557 0.00868 -0.0027 0.0632 1.0000 8.750 1.0692 0.01596 0.00913 -0.0023 0.0613 1.0000 9.000 1.0938 0.01640 0.00961 -0.0019 0.0590 1.0000 9.250 1.1177 0.01691 0.01013 -0.0015 0.0569 1.0000 9.500 1.1387 0.01784 0.01105 -0.0009 0.0545 1.0000 9.750 1.1631 0.01824 0.01154 -0.0005 0.0530 1.0000 10.000 1.1865 0.01876 0.01211 -0.0001 0.0512 1.0000 10.250 1.2094 0.01933 0.01271 0.0004 0.0497 1.0000 10.500 1.2296 0.02023 0.01361 0.0011 0.0480 1.0000 10.750 1.2502 0.02107 0.01452 0.0018 0.0467 1.0000 11.000 1.2724 0.02164 0.01519 0.0023 0.0454 1.0000 11.250 1.2936 0.02228 0.01590 0.0029 0.0441 1.0000 11.500 1.3140 0.02299 0.01664 0.0035 0.0430 1.0000 11.750 1.3321 0.02392 0.01760 0.0043 0.0419 1.0000 12.000 1.3466 0.02534 0.01907 0.0054 0.0408 1.0000 12.250 1.3651 0.02609 0.01995 0.0062 0.0400 1.0000 12.500 1.3820 0.02695 0.02092 0.0071 0.0391 1.0000 12.750 1.3976 0.02784 0.02190 0.0080 0.0381 1.0000 13.000 1.4103 0.02878 0.02291 0.0093 0.0374 1.0000 13.250 1.4206 0.02990 0.02408 0.0106 0.0367 1.0000 13.500 1.4279 0.03137 0.02560 0.0118 0.0361 1.0000 13.750 1.4295 0.03366 0.02796 0.0131 0.0354 1.0000 14.000 1.4362 0.03525 0.02971 0.0138 0.0350 1.0000 14.250 1.4412 0.03713 0.03174 0.0142 0.0345 1.0000 14.500 1.4448 0.03928 0.03403 0.0143 0.0341 1.0000 14.750 1.4471 0.04166 0.03656 0.0141 0.0336 1.0000 15.000 1.4487 0.04427 0.03929 0.0136 0.0331 1.0000 15.250 1.4494 0.04710 0.04223 0.0128 0.0326 1.0000 15.500 1.4494 0.05013 0.04537 0.0117 0.0322 1.0000 15.750 1.4481 0.05341 0.04873 0.0105 0.0318 1.0000 16.000 1.4452 0.05698 0.05240 0.0090 0.0315 1.0000 16.250 1.4402 0.06087 0.05637 0.0075 0.0312 1.0000 16.500 1.4321 0.06522 0.06082 0.0058 0.0309 1.0000 16.750 1.4185 0.07038 0.06610 0.0039 0.0306 1.0000 17.000 1.4010 0.07639 0.07228 0.0011 0.0304 1.0000 17.250 1.3850 0.08265 0.07871 -0.0024 0.0303 1.0000 17.500 1.3663 0.08961 0.08585 -0.0064 0.0302 1.0000 17.750 1.3445 0.09743 0.09385 -0.0110 0.0301 1.0000 18.000 1.3187 0.10633 0.10293 -0.0163 0.0300 1.0000 18.250 1.2865 0.11701 0.11381 -0.0228 0.0300 1.0000 18.500 1.2398 0.13135 0.12838 -0.0317 0.0301 1.0000