XFOIL Version 6.96 Calculated polar for: GIII BL332 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.5936 0.08159 0.07999 -0.0090 1.0000 0.0145 -8.500 -0.6014 0.07523 0.07363 -0.0168 1.0000 0.0146 -8.250 -0.6016 0.06981 0.06816 -0.0212 1.0000 0.0150 -7.750 -0.5917 0.05592 0.05391 -0.0278 1.0000 0.0166 -7.500 -0.5850 0.05078 0.04859 -0.0280 1.0000 0.0167 -7.250 -0.5773 0.04597 0.04358 -0.0276 1.0000 0.0167 -6.000 -0.5226 0.02193 0.01800 -0.0218 0.9948 0.0157 -5.750 -0.4964 0.01679 0.01221 -0.0219 0.9910 0.0161 -5.500 -0.4644 0.01500 0.01014 -0.0229 0.9879 0.0164 -5.250 -0.4307 0.01408 0.00907 -0.0243 0.9853 0.0167 -5.000 -0.4017 0.01193 0.00672 -0.0248 0.9808 0.0175 -4.750 -0.3707 0.01157 0.00636 -0.0256 0.9746 0.0181 -4.500 -0.3395 0.01130 0.00607 -0.0264 0.9681 0.0189 -4.250 -0.3113 0.01085 0.00558 -0.0264 0.9583 0.0198 -4.000 -0.2849 0.01040 0.00507 -0.0259 0.9475 0.0205 -3.750 -0.2584 0.01014 0.00475 -0.0255 0.9377 0.0211 -3.500 -0.2348 0.00927 0.00381 -0.0246 0.9271 0.0224 -3.250 -0.2089 0.00902 0.00356 -0.0242 0.9164 0.0235 -3.000 -0.1826 0.00882 0.00333 -0.0238 0.9063 0.0248 -2.500 -0.1288 0.00866 0.00311 -0.0231 0.8851 0.0272 -2.250 -0.1045 0.00801 0.00239 -0.0224 0.8734 0.0297 -2.000 -0.0779 0.00785 0.00219 -0.0220 0.8624 0.0314 -1.750 -0.0511 0.00771 0.00202 -0.0217 0.8516 0.0332 -1.500 -0.0239 0.00761 0.00190 -0.0215 0.8407 0.0346 -1.250 0.0028 0.00739 0.00161 -0.0212 0.8295 0.0367 -1.000 0.0296 0.00723 0.00142 -0.0209 0.8169 0.0399 -0.750 0.0567 0.00714 0.00129 -0.0206 0.8031 0.0428 -0.500 0.0839 0.00708 0.00118 -0.0204 0.7895 0.0453 0.000 0.1228 0.00469 0.00090 -0.0179 0.7633 0.7360 0.250 0.1464 0.00450 0.00093 -0.0167 0.7493 0.8135 0.500 0.1720 0.00447 0.00094 -0.0160 0.7332 0.8448 0.750 0.1974 0.00446 0.00095 -0.0153 0.7159 0.8726 1.000 0.2235 0.00448 0.00097 -0.0147 0.6988 0.8937 1.250 0.2488 0.00450 0.00102 -0.0138 0.6796 0.9186 1.500 0.2739 0.00461 0.00105 -0.0130 0.6471 0.9391 1.750 0.2999 0.00477 0.00109 -0.0124 0.6062 0.9561 2.000 0.3286 0.00497 0.00115 -0.0125 0.5659 0.9702 2.250 0.3615 0.00517 0.00122 -0.0137 0.5289 0.9761 2.500 0.3917 0.00541 0.00130 -0.0143 0.4911 0.9834 2.750 0.4265 0.00563 0.00139 -0.0159 0.4571 0.9863 3.000 0.4609 0.00588 0.00148 -0.0176 0.4151 0.9895 3.250 0.4937 0.00622 0.00160 -0.0189 0.3583 0.9933 3.500 0.5274 0.00661 0.00174 -0.0205 0.3007 0.9959 3.750 0.5612 0.00705 0.00193 -0.0222 0.2398 0.9985 4.000 0.5908 0.00749 0.00212 -0.0230 0.1847 1.0000 4.250 0.6128 0.00789 0.00232 -0.0221 0.1420 1.0000 4.500 0.6352 0.00825 0.00253 -0.0212 0.1093 1.0000 4.750 0.6580 0.00859 0.00275 -0.0203 0.0869 1.0000 5.000 0.6814 0.00887 0.00296 -0.0195 0.0734 1.0000 5.250 0.7054 0.00911 0.00317 -0.0188 0.0651 1.0000 5.500 0.7294 0.00936 0.00341 -0.0181 0.0575 1.0000 5.750 0.7530 0.00970 0.00368 -0.0174 0.0489 1.0000 6.000 0.7777 0.00990 0.00389 -0.0169 0.0448 1.0000 6.250 0.8015 0.01027 0.00422 -0.0162 0.0388 1.0000 6.500 0.8265 0.01051 0.00448 -0.0157 0.0360 1.0000 6.750 0.8505 0.01092 0.00486 -0.0151 0.0318 1.0000 7.000 0.8752 0.01124 0.00521 -0.0146 0.0297 1.0000 7.250 0.9001 0.01153 0.00552 -0.0142 0.0277 1.0000 7.500 0.9241 0.01197 0.00596 -0.0137 0.0255 1.0000 7.750 0.9475 0.01252 0.00656 -0.0130 0.0238 1.0000 8.000 0.9722 0.01285 0.00694 -0.0126 0.0230 1.0000 8.250 0.9968 0.01322 0.00735 -0.0122 0.0219 1.0000 8.500 1.0211 0.01361 0.00775 -0.0118 0.0207 1.0000 8.750 1.0434 0.01428 0.00845 -0.0111 0.0195 1.0000 9.000 1.0647 0.01509 0.00934 -0.0102 0.0186 1.0000 9.250 1.0886 0.01551 0.00983 -0.0098 0.0182 1.0000 9.500 1.1120 0.01599 0.01037 -0.0093 0.0175 1.0000 9.750 1.1354 0.01645 0.01087 -0.0088 0.0168 1.0000 10.000 1.1586 0.01692 0.01137 -0.0083 0.0161 1.0000 10.250 1.1801 0.01757 0.01206 -0.0077 0.0155 1.0000 10.500 1.1950 0.01908 0.01370 -0.0062 0.0146 1.0000 10.750 1.2160 0.01976 0.01447 -0.0054 0.0143 1.0000 11.000 1.2373 0.02036 0.01515 -0.0047 0.0140 1.0000 11.250 1.2581 0.02099 0.01586 -0.0040 0.0135 1.0000 11.500 1.2785 0.02162 0.01656 -0.0033 0.0130 1.0000 11.750 1.2985 0.02224 0.01725 -0.0026 0.0126 1.0000 12.000 1.3174 0.02293 0.01799 -0.0017 0.0122 1.0000 12.250 1.3338 0.02383 0.01896 -0.0006 0.0118 1.0000 12.500 1.3422 0.02547 0.02072 0.0013 0.0113 1.0000 12.750 1.3433 0.02749 0.02293 0.0041 0.0110 1.0000 13.000 1.3548 0.02841 0.02395 0.0057 0.0109 1.0000 13.250 1.3638 0.02953 0.02518 0.0073 0.0107 1.0000 13.500 1.3707 0.03087 0.02665 0.0088 0.0105 1.0000 13.750 1.3758 0.03244 0.02835 0.0102 0.0103 1.0000 14.000 1.3796 0.03424 0.03027 0.0113 0.0101 1.0000 14.250 1.3818 0.03631 0.03247 0.0120 0.0099 1.0000 14.500 1.3838 0.03853 0.03481 0.0123 0.0097 1.0000 14.750 1.3851 0.04102 0.03740 0.0122 0.0095 1.0000 15.000 1.3848 0.04384 0.04034 0.0117 0.0093 1.0000 15.250 1.3839 0.04698 0.04357 0.0108 0.0092 1.0000 15.500 1.3792 0.05081 0.04751 0.0093 0.0091 1.0000 15.750 1.3707 0.05549 0.05233 0.0070 0.0090 1.0000 16.000 1.3589 0.06099 0.05796 0.0041 0.0089 1.0000 16.250 1.3413 0.06783 0.06495 0.0003 0.0088 1.0000 16.500 1.3191 0.07567 0.07295 -0.0042 0.0088 1.0000 16.750 1.2926 0.08469 0.08214 -0.0093 0.0089 1.0000 17.000 1.2536 0.09642 0.09407 -0.0157 0.0090 1.0000 17.250 1.1967 0.11232 0.11022 -0.0243 0.0092 1.0000