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 = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -7.750 -0.5200 0.08900 0.08547 0.0057 1.0000 0.0414 -7.500 -0.5181 0.08406 0.08053 -0.0020 1.0000 0.0422 -7.250 -0.5150 0.07863 0.07480 -0.0135 1.0000 0.0428 -7.000 -0.5048 0.07397 0.07015 -0.0142 1.0000 0.0431 -6.750 -0.4930 0.07028 0.06655 -0.0135 1.0000 0.0434 -6.500 -0.4810 0.06703 0.06331 -0.0136 1.0000 0.0441 -6.250 -0.4675 0.06378 0.06004 -0.0146 1.0000 0.0451 -6.000 -0.4521 0.06039 0.05656 -0.0162 1.0000 0.0467 -5.750 -0.4294 0.05836 0.05376 -0.0193 1.0000 0.0493 -5.500 -0.4148 0.05317 0.04878 -0.0196 1.0000 0.0498 -5.250 -0.3990 0.04987 0.04553 -0.0196 1.0000 0.0504 -5.000 -0.3818 0.04714 0.04278 -0.0196 1.0000 0.0515 -4.750 -0.3632 0.04464 0.04018 -0.0195 1.0000 0.0532 -4.500 -0.3400 0.04422 0.03905 -0.0181 1.0000 0.0570 -4.250 -0.3285 0.04011 0.03513 -0.0174 1.0000 0.0577 -4.000 -0.3184 0.03788 0.03296 -0.0157 1.0000 0.0588 -3.750 -0.3084 0.03627 0.03132 -0.0137 1.0000 0.0607 -3.500 -0.2742 0.03495 0.02945 -0.0146 0.9954 0.0664 -3.250 -0.2387 0.03149 0.02607 -0.0179 0.9886 0.0685 -3.000 -0.1939 0.03097 0.02499 -0.0205 0.9811 0.0766 -2.750 -0.1573 0.02719 0.02137 -0.0239 0.9737 0.0798 -2.500 -0.1186 0.02566 0.01958 -0.0261 0.9635 0.0902 -2.250 -0.0810 0.02454 0.01822 -0.0279 0.9525 0.1021 -2.000 -0.0470 0.02255 0.01627 -0.0294 0.9405 0.1107 -0.500 0.1137 0.01741 0.00977 -0.0207 0.8272 0.0879 -0.250 0.1384 0.01566 0.00804 -0.0194 0.8050 0.0830 0.000 0.1640 0.01492 0.00720 -0.0181 0.7814 0.0811 0.250 0.1894 0.01441 0.00660 -0.0169 0.7580 0.0831 0.500 0.2150 0.01390 0.00600 -0.0158 0.7335 0.0836 0.750 0.2406 0.01347 0.00549 -0.0148 0.7093 0.0847 1.000 0.2665 0.01327 0.00517 -0.0138 0.6873 0.0875 1.250 0.2914 0.01275 0.00466 -0.0130 0.6660 0.0904 1.500 0.3170 0.01247 0.00436 -0.0122 0.6450 0.0936 1.750 0.3430 0.01234 0.00417 -0.0116 0.6249 0.0992 2.000 0.3689 0.01217 0.00392 -0.0109 0.6055 0.1048 2.250 0.3954 0.01212 0.00378 -0.0104 0.5864 0.1133 2.500 0.4217 0.01204 0.00365 -0.0098 0.5671 0.1320 2.750 0.4683 0.00986 0.00372 -0.0128 0.5420 1.0000 3.000 0.4933 0.01002 0.00372 -0.0120 0.5190 1.0000 3.250 0.5180 0.01021 0.00374 -0.0112 0.4940 1.0000 3.500 0.5428 0.01039 0.00380 -0.0104 0.4643 1.0000 3.750 0.5675 0.01062 0.00388 -0.0097 0.4288 1.0000 4.000 0.5917 0.01091 0.00397 -0.0089 0.3799 1.0000 4.250 0.6152 0.01138 0.00412 -0.0082 0.3168 1.0000 4.500 0.6383 0.01200 0.00442 -0.0075 0.2710 1.0000 4.750 0.6618 0.01263 0.00482 -0.0069 0.2420 1.0000 5.000 0.6859 0.01318 0.00523 -0.0063 0.2189 1.0000 5.250 0.7101 0.01374 0.00566 -0.0058 0.1994 1.0000 5.500 0.7344 0.01429 0.00610 -0.0053 0.1822 1.0000 5.750 0.7588 0.01482 0.00655 -0.0048 0.1669 1.0000 6.000 0.7834 0.01535 0.00703 -0.0043 0.1535 1.0000 6.250 0.8076 0.01595 0.00758 -0.0038 0.1421 1.0000 6.500 0.8312 0.01665 0.00817 -0.0032 0.1326 1.0000 6.750 0.8559 0.01716 0.00869 -0.0027 0.1243 1.0000 7.000 0.8794 0.01794 0.00942 -0.0022 0.1173 1.0000 7.250 0.9037 0.01852 0.01002 -0.0017 0.1110 1.0000 7.500 0.9268 0.01946 0.01089 -0.0011 0.1056 1.0000 7.750 0.9511 0.02006 0.01157 -0.0006 0.1005 1.0000 8.000 0.9745 0.02083 0.01230 -0.0001 0.0961 1.0000 8.250 0.9977 0.02188 0.01339 0.0005 0.0923 1.0000 8.500 1.0213 0.02260 0.01421 0.0010 0.0884 1.0000 8.750 1.0445 0.02340 0.01498 0.0015 0.0849 1.0000 9.000 1.0668 0.02481 0.01642 0.0020 0.0820 1.0000 9.250 1.0894 0.02570 0.01749 0.0026 0.0791 1.0000 9.500 1.1116 0.02658 0.01846 0.0032 0.0762 1.0000 9.750 1.1339 0.02763 0.01947 0.0036 0.0737 1.0000 10.000 1.1543 0.02945 0.02142 0.0042 0.0716 1.0000 10.250 1.1739 0.03069 0.02292 0.0050 0.0696 1.0000 10.500 1.1933 0.03193 0.02434 0.0057 0.0674 1.0000 10.750 1.2128 0.03306 0.02553 0.0063 0.0654 1.0000 11.000 1.2326 0.03463 0.02709 0.0068 0.0638 1.0000 11.250 1.2462 0.03720 0.02991 0.0077 0.0624 1.0000 11.500 1.2565 0.03922 0.03232 0.0090 0.0612 1.0000 11.750 1.2650 0.04144 0.03485 0.0102 0.0598 1.0000 12.000 1.2735 0.04349 0.03713 0.0113 0.0585 1.0000 12.250 1.2840 0.04522 0.03897 0.0122 0.0573 1.0000 12.500 1.2916 0.04718 0.04105 0.0133 0.0563 1.0000 12.750 1.2970 0.04951 0.04348 0.0143 0.0556 1.0000 13.000 1.2937 0.05294 0.04706 0.0155 0.0549 1.0000 13.250 1.2756 0.05712 0.05149 0.0167 0.0547 1.0000 13.500 1.2522 0.06138 0.05602 0.0166 0.0546 1.0000 13.750 1.2260 0.06678 0.06167 0.0148 0.0545 1.0000 14.000 1.1966 0.07351 0.06864 0.0114 0.0546 1.0000 14.250 1.1615 0.08191 0.07729 0.0057 0.0549 1.0000 14.500 0.8792 0.16723 0.16314 -0.0424 0.0828 1.0000