XFOIL Version 6.96 Calculated polar for: GIII BL167 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.6094 0.12138 0.11977 0.0136 1.0000 0.0032 -10.750 -0.6095 0.11652 0.11492 0.0116 1.0000 0.0031 -9.750 -0.8873 0.02772 0.02475 -0.0243 1.0000 0.0027 -9.500 -0.8768 0.02362 0.02022 -0.0229 1.0000 0.0028 -9.250 -0.8583 0.02174 0.01811 -0.0221 1.0000 0.0029 -9.000 -0.8381 0.02034 0.01652 -0.0214 1.0000 0.0030 -8.750 -0.8170 0.01915 0.01516 -0.0206 1.0000 0.0032 -8.500 -0.7958 0.01807 0.01392 -0.0198 1.0000 0.0033 -8.250 -0.7745 0.01703 0.01273 -0.0189 1.0000 0.0035 -8.000 -0.7506 0.01604 0.01155 -0.0186 0.9984 0.0037 -7.750 -0.7212 0.01507 0.01041 -0.0194 0.9935 0.0039 -7.500 -0.6916 0.01422 0.00941 -0.0202 0.9874 0.0041 -7.250 -0.6619 0.01349 0.00855 -0.0210 0.9800 0.0043 -7.000 -0.6325 0.01266 0.00758 -0.0217 0.9710 0.0045 -6.750 -0.6036 0.01196 0.00679 -0.0222 0.9597 0.0051 -6.500 -0.5755 0.01163 0.00642 -0.0224 0.9463 0.0055 -6.250 -0.5491 0.01135 0.00608 -0.0223 0.9317 0.0061 -6.000 -0.5234 0.01108 0.00570 -0.0219 0.9168 0.0068 -5.750 -0.4979 0.01079 0.00532 -0.0215 0.9023 0.0072 -5.500 -0.4725 0.01044 0.00487 -0.0210 0.8887 0.0075 -5.250 -0.4478 0.00989 0.00420 -0.0205 0.8763 0.0086 -5.000 -0.4217 0.00963 0.00388 -0.0202 0.8655 0.0094 -4.750 -0.3955 0.00940 0.00358 -0.0200 0.8552 0.0102 -4.500 -0.3689 0.00920 0.00331 -0.0198 0.8452 0.0111 -4.250 -0.3423 0.00899 0.00303 -0.0196 0.8362 0.0117 -3.750 -0.2893 0.00846 0.00236 -0.0191 0.8201 0.0146 -3.500 -0.2625 0.00826 0.00214 -0.0190 0.8125 0.0172 -3.250 -0.2353 0.00811 0.00194 -0.0189 0.8050 0.0193 -3.000 -0.2084 0.00793 0.00177 -0.0188 0.7982 0.0265 -2.750 -0.1810 0.00780 0.00162 -0.0188 0.7915 0.0316 -2.500 -0.1539 0.00767 0.00149 -0.0187 0.7849 0.0389 -2.250 -0.1264 0.00756 0.00137 -0.0187 0.7782 0.0459 -2.000 -0.0991 0.00745 0.00126 -0.0187 0.7719 0.0550 -1.750 -0.0717 0.00732 0.00117 -0.0186 0.7642 0.0701 -1.500 -0.0448 0.00718 0.00107 -0.0186 0.7541 0.0935 -1.250 -0.0179 0.00705 0.00098 -0.0185 0.7426 0.1223 -1.000 0.0090 0.00686 0.00091 -0.0184 0.7316 0.1679 -0.750 0.0352 0.00658 0.00083 -0.0183 0.7207 0.2484 -0.500 0.0548 0.00534 0.00064 -0.0173 0.7097 0.5915 -0.250 0.0794 0.00505 0.00062 -0.0167 0.6978 0.6894 0.000 0.1057 0.00496 0.00063 -0.0164 0.6866 0.7332 0.250 0.1323 0.00490 0.00064 -0.0161 0.6759 0.7661 0.500 0.1590 0.00486 0.00065 -0.0159 0.6654 0.7909 0.750 0.1850 0.00481 0.00069 -0.0154 0.6545 0.8234 1.000 0.2120 0.00482 0.00071 -0.0152 0.6431 0.8386 1.250 0.2395 0.00486 0.00073 -0.0152 0.6312 0.8459 1.500 0.2670 0.00490 0.00076 -0.0152 0.6186 0.8542 1.750 0.2943 0.00494 0.00081 -0.0151 0.6051 0.8626 2.000 0.3209 0.00506 0.00085 -0.0149 0.5760 0.8716 2.250 0.3449 0.00548 0.00094 -0.0143 0.4774 0.8821 2.500 0.3689 0.00592 0.00111 -0.0137 0.3949 0.8934 2.750 0.3936 0.00630 0.00127 -0.0133 0.3296 0.9049 3.000 0.4189 0.00660 0.00142 -0.0130 0.2799 0.9172 3.250 0.4429 0.00711 0.00163 -0.0125 0.1976 0.9307 3.500 0.4679 0.00759 0.00188 -0.0122 0.1300 0.9439 3.750 0.4949 0.00796 0.00210 -0.0123 0.0876 0.9558 4.000 0.5238 0.00827 0.00232 -0.0128 0.0620 0.9662 4.250 0.5541 0.00853 0.00252 -0.0136 0.0464 0.9746 4.500 0.5853 0.00880 0.00274 -0.0146 0.0342 0.9811 4.750 0.6159 0.00907 0.00299 -0.0154 0.0261 0.9871 5.000 0.6474 0.00934 0.00325 -0.0165 0.0211 0.9917 5.250 0.6783 0.00965 0.00357 -0.0174 0.0173 0.9959 5.500 0.7100 0.00989 0.00383 -0.0186 0.0161 0.9992 5.750 0.7358 0.01015 0.00413 -0.0184 0.0149 1.0000 6.000 0.7594 0.01042 0.00441 -0.0177 0.0134 1.0000 6.250 0.7828 0.01077 0.00476 -0.0170 0.0116 1.0000 6.500 0.8062 0.01116 0.00520 -0.0163 0.0104 1.0000 6.750 0.8307 0.01142 0.00549 -0.0159 0.0098 1.0000 7.000 0.8551 0.01172 0.00583 -0.0154 0.0089 1.0000 7.250 0.8794 0.01204 0.00616 -0.0150 0.0078 1.0000 7.500 0.9028 0.01252 0.00667 -0.0144 0.0065 1.0000 7.750 0.9271 0.01287 0.00706 -0.0140 0.0060 1.0000 8.000 0.9510 0.01329 0.00752 -0.0136 0.0054 1.0000 8.250 0.9747 0.01373 0.00799 -0.0131 0.0048 1.0000 8.500 0.9980 0.01424 0.00853 -0.0126 0.0043 1.0000 8.750 1.0197 0.01499 0.00937 -0.0119 0.0038 1.0000 9.000 1.0420 0.01565 0.01011 -0.0112 0.0036 1.0000 9.250 1.0645 0.01626 0.01081 -0.0106 0.0035 1.0000 9.500 1.0864 0.01694 0.01161 -0.0100 0.0033 1.0000 9.750 1.1078 0.01767 0.01245 -0.0093 0.0031 1.0000 10.000 1.1289 0.01844 0.01332 -0.0086 0.0029 1.0000 10.250 1.1496 0.01922 0.01420 -0.0079 0.0028 1.0000 10.500 1.1702 0.01998 0.01505 -0.0072 0.0026 1.0000 10.750 1.1904 0.02077 0.01593 -0.0065 0.0024 1.0000 11.000 1.2089 0.02174 0.01700 -0.0056 0.0022 1.0000 11.250 1.2238 0.02317 0.01860 -0.0043 0.0021 1.0000 11.500 1.2338 0.02514 0.02083 -0.0025 0.0019 1.0000 11.750 1.2476 0.02645 0.02232 -0.0012 0.0019 1.0000 12.000 1.2591 0.02792 0.02396 0.0003 0.0019 1.0000 12.250 1.2672 0.02951 0.02574 0.0022 0.0018 1.0000 12.500 1.2706 0.03124 0.02765 0.0045 0.0018 1.0000 12.750 1.2709 0.03321 0.02980 0.0067 0.0018 1.0000 13.000 1.2678 0.03557 0.03236 0.0086 0.0018 1.0000 13.250 1.2620 0.03836 0.03535 0.0100 0.0018 1.0000 13.500 1.2533 0.04170 0.03889 0.0106 0.0018 1.0000 13.750 1.2414 0.04575 0.04314 0.0104 0.0017 1.0000 14.000 1.2260 0.05070 0.04829 0.0091 0.0017 1.0000 14.250 1.2064 0.05689 0.05467 0.0063 0.0017 1.0000 14.500 1.1817 0.06490 0.06288 0.0016 0.0017 1.0000 14.750 1.1511 0.07583 0.07400 -0.0060 0.0018 1.0000 15.250 0.9506 0.13527 0.13377 -0.0360 0.0022 1.0000