XFOIL Version 6.96 Calculated polar for: GIII BL288 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 ------ -------- --------- --------- -------- -------- -------- -10.250 -0.6466 0.09422 0.09260 0.0006 1.0000 0.0068 -8.750 -0.8039 0.02116 0.01727 -0.0230 1.0000 0.0090 -8.500 -0.7849 0.01960 0.01548 -0.0219 1.0000 0.0091 -8.250 -0.7641 0.01863 0.01434 -0.0209 1.0000 0.0092 -8.000 -0.7447 0.01683 0.01226 -0.0199 0.9992 0.0095 -7.750 -0.7163 0.01546 0.01070 -0.0206 0.9955 0.0098 -7.500 -0.6872 0.01461 0.00973 -0.0213 0.9912 0.0100 -7.250 -0.6572 0.01391 0.00893 -0.0221 0.9867 0.0102 -7.000 -0.6276 0.01327 0.00820 -0.0228 0.9812 0.0104 -6.750 -0.5972 0.01268 0.00753 -0.0236 0.9754 0.0106 -6.500 -0.5680 0.01219 0.00698 -0.0241 0.9671 0.0110 -6.250 -0.5393 0.01175 0.00647 -0.0244 0.9581 0.0113 -6.000 -0.5120 0.01126 0.00590 -0.0244 0.9476 0.0116 -5.750 -0.4861 0.01081 0.00536 -0.0240 0.9356 0.0119 -5.500 -0.4605 0.01043 0.00489 -0.0236 0.9235 0.0122 -5.250 -0.4349 0.01009 0.00447 -0.0232 0.9119 0.0125 -5.000 -0.4090 0.00980 0.00411 -0.0228 0.9014 0.0127 -4.750 -0.3837 0.00939 0.00360 -0.0223 0.8911 0.0132 -4.500 -0.3575 0.00912 0.00329 -0.0219 0.8803 0.0139 -4.250 -0.3310 0.00891 0.00304 -0.0217 0.8696 0.0145 -4.000 -0.3045 0.00873 0.00281 -0.0214 0.8593 0.0152 -3.750 -0.2778 0.00855 0.00258 -0.0211 0.8490 0.0161 -3.500 -0.2508 0.00839 0.00237 -0.0210 0.8393 0.0170 -3.250 -0.2241 0.00821 0.00217 -0.0207 0.8297 0.0188 -3.000 -0.1969 0.00810 0.00205 -0.0206 0.8197 0.0209 -2.750 -0.1696 0.00800 0.00192 -0.0205 0.8112 0.0225 -2.500 -0.1423 0.00789 0.00177 -0.0203 0.8028 0.0237 -2.250 -0.1152 0.00774 0.00160 -0.0202 0.7925 0.0262 -2.000 -0.0880 0.00765 0.00148 -0.0201 0.7806 0.0283 -1.750 -0.0607 0.00758 0.00137 -0.0199 0.7677 0.0301 -1.500 -0.0333 0.00753 0.00129 -0.0198 0.7561 0.0316 -1.250 -0.0060 0.00743 0.00116 -0.0197 0.7451 0.0360 -1.000 0.0214 0.00735 0.00108 -0.0196 0.7331 0.0400 -0.750 0.0488 0.00731 0.00100 -0.0195 0.7195 0.0442 -0.500 0.0760 0.00724 0.00094 -0.0194 0.7048 0.0573 -0.250 0.1016 0.00684 0.00086 -0.0191 0.6902 0.1809 0.000 0.1177 0.00517 0.00070 -0.0176 0.6767 0.6705 0.250 0.1429 0.00503 0.00072 -0.0170 0.6618 0.7426 0.500 0.1697 0.00502 0.00073 -0.0167 0.6464 0.7663 0.750 0.1966 0.00504 0.00075 -0.0165 0.6293 0.7853 1.000 0.2227 0.00503 0.00078 -0.0160 0.6092 0.8137 1.250 0.2481 0.00505 0.00082 -0.0154 0.5840 0.8456 1.500 0.2739 0.00520 0.00087 -0.0150 0.5412 0.8609 1.750 0.2991 0.00550 0.00094 -0.0145 0.4766 0.8705 2.000 0.3248 0.00575 0.00103 -0.0142 0.4264 0.8808 2.500 0.3756 0.00634 0.00126 -0.0134 0.3161 0.9053 2.750 0.4009 0.00664 0.00139 -0.0130 0.2659 0.9195 3.000 0.4269 0.00688 0.00153 -0.0127 0.2309 0.9344 3.250 0.4536 0.00715 0.00168 -0.0126 0.1937 0.9479 3.500 0.4818 0.00746 0.00185 -0.0129 0.1556 0.9592 3.750 0.5111 0.00783 0.00205 -0.0135 0.1144 0.9685 4.000 0.5412 0.00816 0.00226 -0.0142 0.0866 0.9765 4.250 0.5723 0.00841 0.00244 -0.0151 0.0708 0.9828 4.500 0.6036 0.00866 0.00263 -0.0161 0.0587 0.9879 4.750 0.6347 0.00893 0.00284 -0.0170 0.0473 0.9926 5.000 0.6663 0.00918 0.00306 -0.0181 0.0399 0.9963 5.250 0.6980 0.00944 0.00328 -0.0192 0.0345 0.9995 5.500 0.7235 0.00965 0.00350 -0.0188 0.0321 1.0000 5.750 0.7478 0.00986 0.00372 -0.0182 0.0302 1.0000 6.000 0.7720 0.01011 0.00397 -0.0176 0.0278 1.0000 6.250 0.7962 0.01041 0.00426 -0.0170 0.0249 1.0000 6.500 0.8210 0.01065 0.00453 -0.0166 0.0237 1.0000 6.750 0.8459 0.01089 0.00479 -0.0162 0.0226 1.0000 7.000 0.8708 0.01117 0.00508 -0.0157 0.0210 1.0000 7.250 0.8954 0.01149 0.00540 -0.0153 0.0192 1.0000 7.500 0.9198 0.01185 0.00578 -0.0149 0.0175 1.0000 7.750 0.9447 0.01214 0.00610 -0.0145 0.0166 1.0000 8.000 0.9694 0.01247 0.00647 -0.0141 0.0156 1.0000 8.250 0.9938 0.01283 0.00682 -0.0137 0.0144 1.0000 8.500 1.0176 0.01328 0.00729 -0.0133 0.0131 1.0000 8.750 1.0418 0.01368 0.00774 -0.0128 0.0126 1.0000 9.000 1.0659 0.01408 0.00819 -0.0124 0.0121 1.0000 9.250 1.0898 0.01449 0.00865 -0.0120 0.0115 1.0000 9.500 1.1135 0.01492 0.00911 -0.0116 0.0108 1.0000 9.750 1.1368 0.01540 0.00961 -0.0111 0.0100 1.0000 10.000 1.1587 0.01605 0.01031 -0.0105 0.0093 1.0000 10.250 1.1818 0.01651 0.01085 -0.0100 0.0091 1.0000 10.500 1.2044 0.01702 0.01144 -0.0095 0.0087 1.0000 10.750 1.2266 0.01756 0.01205 -0.0089 0.0083 1.0000 11.000 1.2485 0.01813 0.01268 -0.0083 0.0079 1.0000 11.250 1.2698 0.01873 0.01333 -0.0077 0.0075 1.0000 11.500 1.2904 0.01939 0.01404 -0.0070 0.0070 1.0000 11.750 1.3091 0.02025 0.01497 -0.0061 0.0065 1.0000 12.000 1.3292 0.02089 0.01570 -0.0053 0.0063 1.0000 12.250 1.3483 0.02160 0.01651 -0.0045 0.0061 1.0000 12.500 1.3664 0.02237 0.01737 -0.0036 0.0058 1.0000 12.750 1.3836 0.02318 0.01827 -0.0026 0.0056 1.0000 13.000 1.3996 0.02405 0.01922 -0.0014 0.0053 1.0000 13.250 1.4138 0.02497 0.02023 -0.0001 0.0051 1.0000 13.500 1.4249 0.02598 0.02132 0.0016 0.0049 1.0000 13.750 1.4332 0.02716 0.02260 0.0036 0.0047 1.0000 14.000 1.4381 0.02862 0.02418 0.0055 0.0045 1.0000 14.250 1.4425 0.03016 0.02585 0.0073 0.0044 1.0000 14.500 1.4473 0.03175 0.02757 0.0086 0.0043 1.0000 14.750 1.4503 0.03360 0.02955 0.0098 0.0043 1.0000 15.000 1.4519 0.03569 0.03178 0.0106 0.0042 1.0000 15.250 1.4515 0.03814 0.03437 0.0111 0.0041 1.0000 15.500 1.4492 0.04096 0.03733 0.0111 0.0041 1.0000 15.750 1.4445 0.04428 0.04079 0.0107 0.0040 1.0000 16.000 1.4374 0.04814 0.04480 0.0097 0.0039 1.0000 16.250 1.4270 0.05277 0.04958 0.0079 0.0039 1.0000 16.500 1.4125 0.05836 0.05533 0.0053 0.0039 1.0000 16.750 1.3928 0.06532 0.06246 0.0015 0.0039 1.0000 17.000 1.3662 0.07402 0.07134 -0.0035 0.0039 1.0000 17.250 1.3276 0.08565 0.08317 -0.0103 0.0039 1.0000 17.500 1.2694 0.10172 0.09947 -0.0192 0.0041 1.0000 17.750 1.1749 0.12605 0.12402 -0.0317 0.0043 1.0000 18.000 1.0933 0.14921 0.14736 -0.0438 0.0046 1.0000