XFOIL Version 6.96 Calculated polar for: DEFIANT CANARD BL145 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.750 -0.4578 0.08794 0.08412 -0.0288 1.0000 0.0163 -9.500 -0.4598 0.08406 0.08029 -0.0303 1.0000 0.0161 -9.250 -0.4736 0.07697 0.07325 -0.0342 1.0000 0.0162 -9.000 -0.4937 0.06757 0.06388 -0.0414 1.0000 0.0163 -8.750 -0.5189 0.06172 0.05798 -0.0446 1.0000 0.0161 -8.500 -0.5341 0.05846 0.05467 -0.0434 1.0000 0.0159 -8.250 -0.5515 0.05357 0.04962 -0.0425 1.0000 0.0159 -8.000 -0.5622 0.04927 0.04512 -0.0409 1.0000 0.0158 -7.750 -0.5677 0.04537 0.04099 -0.0389 1.0000 0.0156 -7.500 -0.5702 0.04148 0.03682 -0.0365 1.0000 0.0155 -7.250 -0.5700 0.03765 0.03264 -0.0340 1.0000 0.0154 -7.000 -0.5653 0.03436 0.02899 -0.0315 1.0000 0.0151 -6.750 -0.5578 0.03128 0.02552 -0.0289 1.0000 0.0149 -6.500 -0.5298 0.02791 0.02160 -0.0301 0.9958 0.0146 -6.250 -0.4984 0.02534 0.01857 -0.0315 0.9911 0.0145 -6.000 -0.4660 0.02338 0.01627 -0.0327 0.9860 0.0146 -5.750 -0.4336 0.02183 0.01448 -0.0338 0.9802 0.0147 -5.500 -0.3998 0.02050 0.01295 -0.0350 0.9746 0.0148 -4.500 -0.2797 0.01651 0.00859 -0.0364 0.9343 0.0161 -4.250 -0.2484 0.01576 0.00777 -0.0369 0.9221 0.0165 -4.000 -0.2143 0.01501 0.00703 -0.0381 0.9096 0.0173 -3.750 -0.1757 0.01439 0.00635 -0.0402 0.8966 0.0183 -3.500 -0.1353 0.01383 0.00573 -0.0427 0.8813 0.0206 -3.250 -0.0934 0.01330 0.00512 -0.0453 0.8610 0.0238 -3.000 -0.0531 0.01279 0.00452 -0.0476 0.8359 0.0287 -2.750 -0.0203 0.01228 0.00403 -0.0484 0.8070 0.0531 -2.500 0.0076 0.01179 0.00370 -0.0484 0.7787 0.1218 -2.250 0.0262 0.01070 0.00344 -0.0471 0.7536 0.3364 -2.000 0.0450 0.01011 0.00341 -0.0452 0.7296 0.5048 -1.750 0.0672 0.00991 0.00336 -0.0436 0.7073 0.5767 -1.500 0.0905 0.00982 0.00331 -0.0423 0.6865 0.6272 -1.250 0.1139 0.00976 0.00329 -0.0409 0.6666 0.6784 -1.000 0.1370 0.00971 0.00326 -0.0394 0.6473 0.7311 -0.750 0.1609 0.00962 0.00325 -0.0379 0.6277 0.7823 -0.500 0.1879 0.00962 0.00324 -0.0372 0.6070 0.8214 -0.250 0.2185 0.00968 0.00323 -0.0373 0.5892 0.8496 0.000 0.2554 0.00977 0.00325 -0.0388 0.5730 0.8783 0.250 0.2894 0.00989 0.00325 -0.0398 0.5572 0.9077 0.500 0.3293 0.01002 0.00327 -0.0421 0.5400 0.9267 1.000 0.4028 0.01030 0.00331 -0.0455 0.5069 0.9609 1.250 0.4403 0.01044 0.00334 -0.0475 0.4913 0.9732 1.500 0.4770 0.01058 0.00338 -0.0493 0.4755 0.9851 1.750 0.5144 0.01073 0.00343 -0.0514 0.4588 0.9955 2.000 0.5446 0.01088 0.00348 -0.0520 0.4428 1.0000 2.250 0.5662 0.01103 0.00354 -0.0507 0.4275 1.0000 2.500 0.5880 0.01120 0.00362 -0.0494 0.4130 1.0000 2.750 0.6100 0.01138 0.00372 -0.0482 0.3984 1.0000 3.000 0.6319 0.01158 0.00384 -0.0470 0.3831 1.0000 3.250 0.6540 0.01179 0.00397 -0.0458 0.3668 1.0000 3.500 0.6761 0.01201 0.00411 -0.0446 0.3508 1.0000 3.750 0.6982 0.01224 0.00429 -0.0434 0.3356 1.0000 4.000 0.7204 0.01248 0.00447 -0.0423 0.3219 1.0000 4.250 0.7423 0.01275 0.00466 -0.0411 0.3078 1.0000 4.500 0.7639 0.01304 0.00487 -0.0399 0.2933 1.0000 4.750 0.7854 0.01335 0.00510 -0.0386 0.2795 1.0000 5.000 0.8072 0.01365 0.00534 -0.0375 0.2680 1.0000 5.250 0.8294 0.01394 0.00560 -0.0364 0.2579 1.0000 5.500 0.8508 0.01428 0.00587 -0.0352 0.2487 1.0000 5.750 0.8735 0.01456 0.00618 -0.0342 0.2411 1.0000 6.000 0.8950 0.01492 0.00649 -0.0331 0.2340 1.0000 6.250 0.9178 0.01520 0.00681 -0.0322 0.2274 1.0000 6.500 0.9398 0.01554 0.00715 -0.0311 0.2199 1.0000 6.750 0.9618 0.01587 0.00750 -0.0301 0.2125 1.0000 7.000 0.9839 0.01618 0.00783 -0.0291 0.2032 1.0000 7.250 1.0061 0.01649 0.00819 -0.0281 0.1941 1.0000 7.500 1.0275 0.01683 0.00853 -0.0270 0.1831 1.0000 7.750 1.0489 0.01718 0.00888 -0.0260 0.1693 1.0000 8.000 1.0696 0.01758 0.00927 -0.0248 0.1523 1.0000 8.250 1.0883 0.01812 0.00973 -0.0235 0.1325 1.0000 8.500 1.1053 0.01879 0.01030 -0.0219 0.1153 1.0000 8.750 1.1219 0.01950 0.01096 -0.0203 0.1036 1.0000 9.000 1.1382 0.02020 0.01164 -0.0186 0.0953 1.0000 9.250 1.1544 0.02087 0.01235 -0.0169 0.0895 1.0000 9.500 1.1689 0.02162 0.01311 -0.0150 0.0843 1.0000 9.750 1.1832 0.02235 0.01388 -0.0131 0.0804 1.0000 10.000 1.1967 0.02305 0.01465 -0.0111 0.0770 1.0000 10.250 1.2068 0.02385 0.01548 -0.0086 0.0741 1.0000 10.500 1.2144 0.02477 0.01644 -0.0059 0.0719 1.0000 10.750 1.2256 0.02555 0.01732 -0.0037 0.0698 1.0000 11.000 1.2352 0.02644 0.01830 -0.0015 0.0677 1.0000 11.250 1.2435 0.02743 0.01937 0.0006 0.0660 1.0000 11.500 1.2497 0.02860 0.02059 0.0028 0.0644 1.0000 11.750 1.2531 0.03001 0.02204 0.0049 0.0630 1.0000 12.000 1.2603 0.03128 0.02342 0.0065 0.0617 1.0000 12.250 1.2673 0.03263 0.02489 0.0078 0.0604 1.0000 12.500 1.2729 0.03417 0.02653 0.0091 0.0591 1.0000 12.750 1.2779 0.03584 0.02829 0.0100 0.0580 1.0000 13.000 1.2819 0.03769 0.03024 0.0108 0.0569 1.0000 13.250 1.2850 0.03972 0.03234 0.0114 0.0560 1.0000 13.500 1.2871 0.04193 0.03461 0.0118 0.0552 1.0000 13.750 1.2890 0.04425 0.03697 0.0122 0.0545 1.0000 14.000 1.2926 0.04650 0.03937 0.0123 0.0538 1.0000 14.250 1.2956 0.04887 0.04188 0.0123 0.0531 1.0000 14.500 1.2978 0.05139 0.04453 0.0121 0.0524 1.0000 14.750 1.2994 0.05402 0.04729 0.0119 0.0516 1.0000 15.000 1.2999 0.05683 0.05022 0.0114 0.0508 1.0000 15.250 1.3002 0.05972 0.05323 0.0108 0.0502 1.0000 15.500 1.2990 0.06285 0.05645 0.0099 0.0493 1.0000 15.750 1.2978 0.06604 0.05972 0.0090 0.0486 1.0000 16.000 1.2963 0.06932 0.06306 0.0079 0.0478 1.0000 16.250 1.2964 0.07235 0.06614 0.0072 0.0472 1.0000 16.500 1.2902 0.07661 0.07060 0.0054 0.0465 1.0000 16.750 1.2821 0.08131 0.07550 0.0032 0.0457 1.0000 17.000 1.2749 0.08596 0.08031 0.0010 0.0449 1.0000