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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.250 -0.6118 0.09345 0.09173 0.0157 1.0000 0.0112 -9.000 -0.6155 0.08818 0.08648 0.0121 1.0000 0.0112 -8.000 -0.7357 0.01640 0.01173 -0.0177 1.0000 0.0162 -7.750 -0.7023 0.01576 0.01103 -0.0190 0.9625 0.0166 -7.500 -0.6727 0.01530 0.01049 -0.0194 0.9324 0.0169 -7.250 -0.6475 0.01484 0.00991 -0.0187 0.9140 0.0172 -7.000 -0.6220 0.01432 0.00930 -0.0182 0.9012 0.0175 -6.750 -0.5962 0.01378 0.00866 -0.0178 0.8906 0.0179 -6.500 -0.5703 0.01322 0.00798 -0.0173 0.8808 0.0184 -6.250 -0.5442 0.01266 0.00730 -0.0169 0.8706 0.0188 -6.000 -0.5179 0.01218 0.00673 -0.0165 0.8611 0.0192 -5.750 -0.4912 0.01188 0.00639 -0.0161 0.8513 0.0196 -5.500 -0.4642 0.01165 0.00612 -0.0158 0.8419 0.0199 -5.250 -0.4373 0.01141 0.00583 -0.0154 0.8312 0.0203 -5.000 -0.4103 0.01113 0.00550 -0.0151 0.8208 0.0207 -4.750 -0.3833 0.01086 0.00515 -0.0147 0.8109 0.0213 -4.500 -0.3562 0.01056 0.00479 -0.0144 0.8004 0.0218 -4.250 -0.3292 0.01027 0.00442 -0.0140 0.7898 0.0222 -4.000 -0.3022 0.01000 0.00410 -0.0137 0.7769 0.0227 -3.750 -0.2748 0.00983 0.00390 -0.0134 0.7613 0.0231 -3.500 -0.2475 0.00968 0.00369 -0.0131 0.7431 0.0236 -3.250 -0.2201 0.00954 0.00348 -0.0128 0.7227 0.0242 -3.000 -0.1928 0.00940 0.00325 -0.0125 0.6993 0.0248 -2.750 -0.1657 0.00926 0.00300 -0.0122 0.6753 0.0254 -2.500 -0.1387 0.00911 0.00274 -0.0119 0.6479 0.0259 -2.250 -0.1115 0.00904 0.00258 -0.0116 0.6178 0.0265 -2.000 -0.0841 0.00900 0.00246 -0.0113 0.5901 0.0271 -1.750 -0.0566 0.00896 0.00234 -0.0111 0.5669 0.0278 -1.500 -0.0290 0.00890 0.00220 -0.0109 0.5472 0.0286 -1.250 -0.0013 0.00882 0.00205 -0.0107 0.5299 0.0292 -1.000 0.0262 0.00872 0.00191 -0.0105 0.5144 0.0300 -0.750 0.0540 0.00867 0.00182 -0.0103 0.4997 0.0307 -0.500 0.0819 0.00864 0.00175 -0.0101 0.4843 0.0316 -0.250 0.1097 0.00861 0.00168 -0.0099 0.4691 0.0327 0.000 0.1376 0.00859 0.00161 -0.0098 0.4531 0.0336 0.250 0.1653 0.00855 0.00153 -0.0096 0.4374 0.0346 0.500 0.1932 0.00855 0.00150 -0.0095 0.4232 0.0357 0.750 0.2211 0.00856 0.00147 -0.0093 0.4080 0.0370 1.000 0.2490 0.00858 0.00144 -0.0092 0.3917 0.0383 1.250 0.2767 0.00860 0.00142 -0.0090 0.3693 0.0398 1.500 0.3041 0.00872 0.00143 -0.0088 0.3343 0.0412 1.750 0.3304 0.00909 0.00151 -0.0086 0.2628 0.0427 2.000 0.3576 0.00927 0.00158 -0.0085 0.2316 0.0440 2.250 0.3852 0.00936 0.00162 -0.0083 0.2141 0.0463 2.500 0.4128 0.00946 0.00167 -0.0082 0.1983 0.0482 2.750 0.4405 0.00955 0.00172 -0.0081 0.1863 0.0499 3.000 0.4682 0.00963 0.00178 -0.0079 0.1746 0.0527 3.250 0.4957 0.00975 0.00185 -0.0078 0.1613 0.0555 3.500 0.5233 0.00988 0.00194 -0.0077 0.1482 0.0584 3.750 0.5509 0.00998 0.00203 -0.0076 0.1380 0.0650 4.000 0.5782 0.01006 0.00215 -0.0074 0.1273 0.1071 4.250 0.5959 0.00846 0.00232 -0.0061 0.1179 0.8269 4.500 0.6175 0.00834 0.00248 -0.0043 0.1102 0.9256 4.750 0.6562 0.00850 0.00264 -0.0066 0.1001 0.9853 5.000 0.6942 0.00874 0.00281 -0.0089 0.0912 1.0000 5.250 0.7202 0.00894 0.00297 -0.0085 0.0845 1.0000 5.500 0.7463 0.00916 0.00314 -0.0081 0.0786 1.0000 5.750 0.7725 0.00937 0.00332 -0.0077 0.0736 1.0000 6.000 0.7988 0.00960 0.00351 -0.0074 0.0693 1.0000 6.250 0.8251 0.00982 0.00370 -0.0071 0.0655 1.0000 6.500 0.8513 0.01008 0.00393 -0.0068 0.0614 1.0000 6.750 0.8778 0.01029 0.00414 -0.0066 0.0593 1.0000 7.000 0.9041 0.01052 0.00436 -0.0063 0.0567 1.0000 7.250 0.9302 0.01080 0.00462 -0.0060 0.0537 1.0000 7.500 0.9566 0.01105 0.00486 -0.0058 0.0518 1.0000 7.750 0.9829 0.01129 0.00511 -0.0056 0.0499 1.0000 8.000 1.0089 0.01157 0.00538 -0.0053 0.0477 1.0000 8.250 1.0347 0.01189 0.00569 -0.0051 0.0454 1.0000 8.500 1.0609 0.01215 0.00596 -0.0049 0.0441 1.0000 8.750 1.0867 0.01244 0.00626 -0.0046 0.0424 1.0000 9.000 1.1124 0.01276 0.00658 -0.0044 0.0407 1.0000 9.250 1.1377 0.01312 0.00693 -0.0041 0.0390 1.0000 9.500 1.1634 0.01342 0.00726 -0.0039 0.0378 1.0000 9.750 1.1887 0.01375 0.00761 -0.0036 0.0365 1.0000 10.000 1.2137 0.01412 0.00798 -0.0033 0.0351 1.0000 10.250 1.2383 0.01455 0.00842 -0.0030 0.0338 1.0000 10.500 1.2631 0.01491 0.00881 -0.0027 0.0330 1.0000 10.750 1.2877 0.01529 0.00922 -0.0024 0.0321 1.0000 11.000 1.3120 0.01569 0.00966 -0.0021 0.0311 1.0000 11.250 1.3358 0.01615 0.01012 -0.0017 0.0300 1.0000 11.500 1.3590 0.01666 0.01066 -0.0013 0.0289 1.0000 11.750 1.3825 0.01712 0.01116 -0.0010 0.0283 1.0000 12.000 1.4057 0.01757 0.01166 -0.0006 0.0277 1.0000 12.250 1.4285 0.01806 0.01220 -0.0001 0.0271 1.0000 12.500 1.4507 0.01859 0.01277 0.0003 0.0264 1.0000 12.750 1.4723 0.01917 0.01338 0.0009 0.0257 1.0000 13.000 1.4930 0.01980 0.01405 0.0014 0.0250 1.0000 13.250 1.5128 0.02050 0.01479 0.0021 0.0244 1.0000 13.500 1.5332 0.02108 0.01544 0.0027 0.0240 1.0000 13.750 1.5527 0.02171 0.01614 0.0034 0.0235 1.0000 14.000 1.5710 0.02241 0.01689 0.0042 0.0230 1.0000 14.250 1.5882 0.02316 0.01771 0.0050 0.0225 1.0000 14.500 1.6034 0.02397 0.01858 0.0060 0.0221 1.0000 14.750 1.6154 0.02488 0.01955 0.0074 0.0217 1.0000 15.000 1.6250 0.02597 0.02070 0.0088 0.0213 1.0000 15.250 1.6322 0.02731 0.02212 0.0099 0.0209 1.0000 15.500 1.6386 0.02883 0.02372 0.0108 0.0206 1.0000 15.750 1.6461 0.03036 0.02535 0.0114 0.0204 1.0000 16.000 1.6525 0.03210 0.02718 0.0117 0.0202 1.0000 16.250 1.6575 0.03409 0.02927 0.0117 0.0199 1.0000 16.500 1.6610 0.03637 0.03166 0.0115 0.0197 1.0000 16.750 1.6625 0.03902 0.03441 0.0109 0.0194 1.0000 17.000 1.6619 0.04210 0.03760 0.0099 0.0192 1.0000 17.250 1.6586 0.04566 0.04127 0.0086 0.0190 1.0000 17.500 1.6524 0.04975 0.04548 0.0069 0.0188 1.0000 17.750 1.6428 0.05440 0.05025 0.0048 0.0187 1.0000 18.000 1.6295 0.05969 0.05566 0.0024 0.0185 1.0000 18.250 1.6115 0.06572 0.06183 -0.0004 0.0184 1.0000 18.500 1.5887 0.07261 0.06886 -0.0037 0.0184 1.0000 18.750 1.5612 0.08049 0.07689 -0.0076 0.0183 1.0000 19.000 1.5292 0.08942 0.08599 -0.0121 0.0183 1.0000 19.250 1.4916 0.09969 0.09642 -0.0174 0.0183 1.0000