XFOIL Version 6.96 Calculated polar for: GIII BL126 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 ------ -------- --------- --------- -------- -------- -------- -8.000 -0.7045 0.03393 0.03134 -0.0218 1.0000 0.0068 -7.750 -0.7112 0.02601 0.02266 -0.0187 1.0000 0.0068 -7.500 -0.7054 0.02110 0.01714 -0.0159 1.0000 0.0070 -7.250 -0.6918 0.01820 0.01386 -0.0138 1.0000 0.0072 -7.000 -0.6737 0.01663 0.01207 -0.0123 1.0000 0.0074 -6.750 -0.6434 0.01549 0.01079 -0.0133 0.9961 0.0078 -6.500 -0.6099 0.01482 0.01004 -0.0149 0.9887 0.0083 -6.250 -0.5761 0.01407 0.00920 -0.0165 0.9784 0.0090 -6.000 -0.5435 0.01318 0.00817 -0.0177 0.9629 0.0096 -5.750 -0.5143 0.01264 0.00749 -0.0180 0.9401 0.0102 -5.250 -0.4697 0.01064 0.00510 -0.0157 0.8913 0.0117 -5.000 -0.4447 0.01026 0.00463 -0.0151 0.8752 0.0127 -4.750 -0.4190 0.00995 0.00424 -0.0147 0.8629 0.0138 -4.500 -0.3927 0.00975 0.00396 -0.0144 0.8528 0.0150 -4.250 -0.3673 0.00930 0.00339 -0.0140 0.8439 0.0161 -4.000 -0.3416 0.00885 0.00286 -0.0135 0.8364 0.0189 -3.750 -0.3150 0.00862 0.00258 -0.0133 0.8297 0.0216 -3.500 -0.2885 0.00832 0.00226 -0.0131 0.8239 0.0287 -3.250 -0.2622 0.00802 0.00201 -0.0128 0.8181 0.0491 -3.000 -0.2356 0.00781 0.00186 -0.0127 0.8128 0.0719 -2.750 -0.2085 0.00762 0.00173 -0.0126 0.8074 0.0921 -2.500 -0.1816 0.00746 0.00161 -0.0125 0.8023 0.1148 -2.250 -0.1547 0.00727 0.00149 -0.0125 0.7976 0.1449 -2.000 -0.1284 0.00696 0.00138 -0.0123 0.7925 0.2028 -1.750 -0.1044 0.00636 0.00123 -0.0119 0.7876 0.3444 -1.500 -0.0870 0.00509 0.00104 -0.0104 0.7820 0.6604 -1.250 -0.0621 0.00487 0.00101 -0.0097 0.7755 0.7309 -1.000 -0.0358 0.00479 0.00100 -0.0093 0.7688 0.7665 -0.750 -0.0089 0.00474 0.00098 -0.0090 0.7619 0.7892 -0.500 0.0183 0.00472 0.00096 -0.0088 0.7553 0.8055 -0.250 0.0454 0.00468 0.00095 -0.0086 0.7480 0.8227 0.000 0.0726 0.00466 0.00094 -0.0084 0.7405 0.8364 0.250 0.0997 0.00463 0.00093 -0.0081 0.7325 0.8505 0.500 0.1269 0.00461 0.00094 -0.0079 0.7253 0.8643 0.750 0.1537 0.00459 0.00095 -0.0076 0.7177 0.8790 1.000 0.1798 0.00457 0.00098 -0.0071 0.7096 0.8993 1.250 0.2061 0.00458 0.00101 -0.0066 0.7012 0.9141 1.500 0.2335 0.00458 0.00103 -0.0064 0.6913 0.9225 1.750 0.2610 0.00460 0.00106 -0.0063 0.6807 0.9308 2.000 0.2881 0.00463 0.00108 -0.0061 0.6688 0.9400 2.250 0.3159 0.00469 0.00112 -0.0060 0.6529 0.9478 2.500 0.3431 0.00479 0.00117 -0.0059 0.6286 0.9565 2.750 0.3720 0.00493 0.00123 -0.0061 0.5987 0.9636 3.000 0.4009 0.00507 0.00130 -0.0064 0.5716 0.9707 3.250 0.4323 0.00529 0.00140 -0.0073 0.5308 0.9755 3.500 0.4585 0.00594 0.00159 -0.0074 0.4094 0.9826 3.750 0.4910 0.00653 0.00184 -0.0090 0.3239 0.9853 4.000 0.5242 0.00695 0.00204 -0.0106 0.2652 0.9879 4.250 0.5560 0.00750 0.00229 -0.0120 0.1926 0.9912 4.500 0.5863 0.00820 0.00263 -0.0132 0.1114 0.9945 4.750 0.6192 0.00879 0.00298 -0.0149 0.0597 0.9966 5.000 0.6522 0.00931 0.00335 -0.0164 0.0299 0.9988 5.250 0.6809 0.00977 0.00379 -0.0169 0.0209 1.0000 5.500 0.7026 0.01001 0.00407 -0.0158 0.0192 1.0000 5.750 0.7241 0.01034 0.00441 -0.0147 0.0170 1.0000 6.000 0.7429 0.01107 0.00524 -0.0130 0.0141 1.0000 6.250 0.7657 0.01131 0.00549 -0.0122 0.0134 1.0000 6.500 0.7878 0.01168 0.00590 -0.0112 0.0125 1.0000 6.750 0.8097 0.01210 0.00636 -0.0102 0.0114 1.0000 7.000 0.8313 0.01260 0.00689 -0.0092 0.0105 1.0000 7.250 0.8474 0.01393 0.00836 -0.0073 0.0094 1.0000 7.500 0.8693 0.01455 0.00905 -0.0064 0.0090 1.0000 7.750 0.8930 0.01492 0.00946 -0.0059 0.0084 1.0000 8.000 0.9157 0.01548 0.01007 -0.0052 0.0078 1.0000 8.250 0.9377 0.01616 0.01081 -0.0044 0.0073 1.0000 8.500 0.9597 0.01684 0.01157 -0.0037 0.0069 1.0000 8.750 0.9807 0.01768 0.01248 -0.0029 0.0066 1.0000 9.000 0.9977 0.01929 0.01423 -0.0016 0.0063 1.0000 9.250 1.0085 0.02244 0.01772 0.0005 0.0059 1.0000 9.500 1.0294 0.02320 0.01860 0.0012 0.0058 1.0000 9.750 1.0480 0.02439 0.01996 0.0022 0.0056 1.0000 10.000 1.0637 0.02605 0.02183 0.0034 0.0053 1.0000 10.250 1.0757 0.02821 0.02424 0.0050 0.0051 1.0000 10.500 1.0819 0.03105 0.02742 0.0071 0.0049 1.0000 10.750 1.0776 0.03504 0.03180 0.0098 0.0049 1.0000 11.000 1.0559 0.04012 0.03729 0.0138 0.0049 1.0000 11.250 1.0267 0.04537 0.04285 0.0165 0.0050 1.0000 11.500 0.9984 0.05114 0.04889 0.0165 0.0051 1.0000 11.750 0.9719 0.05756 0.05552 0.0144 0.0052 1.0000 12.000 0.9477 0.06480 0.06294 0.0101 0.0052 1.0000 12.250 0.9259 0.07321 0.07150 0.0038 0.0052 1.0000