XFOIL Version 6.96 Calculated polar for: Coanda 3 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.750 -0.4466 0.08569 0.08360 -0.0242 1.0000 0.0137 -8.500 -0.4560 0.08329 0.08125 -0.0232 1.0000 0.0140 -8.250 -0.4741 0.08129 0.07930 -0.0209 1.0000 0.0138 -8.000 -0.4873 0.07891 0.07695 -0.0192 1.0000 0.0139 -7.750 -0.4961 0.07591 0.07398 -0.0186 1.0000 0.0139 -7.500 -0.5015 0.07286 0.07093 -0.0184 1.0000 0.0142 -7.250 -0.4870 0.06760 0.06563 -0.0238 0.9979 0.0145 -7.000 -0.4638 0.06135 0.05929 -0.0310 0.9949 0.0152 -6.750 -0.4425 0.05538 0.05318 -0.0364 0.9914 0.0158 -6.500 -0.4196 0.04881 0.04644 -0.0413 0.9874 0.0165 -6.250 -0.3942 0.04196 0.03935 -0.0454 0.9845 0.0174 -4.750 -0.2624 0.01548 0.01007 -0.0443 0.9648 0.0170 -4.500 -0.2325 0.01412 0.00836 -0.0438 0.9621 0.0143 -4.250 -0.2003 0.01302 0.00709 -0.0443 0.9599 0.0149 -4.000 -0.1647 0.01216 0.00613 -0.0458 0.9581 0.0172 -3.750 -0.1256 0.01151 0.00536 -0.0479 0.9567 0.0173 -3.500 -0.1007 0.01112 0.00487 -0.0469 0.9505 0.0172 -3.250 -0.0654 0.01066 0.00427 -0.0481 0.9477 0.0179 -3.000 -0.0278 0.01024 0.00372 -0.0499 0.9458 0.0191 -2.750 0.0120 0.00987 0.00326 -0.0522 0.9444 0.0240 -2.500 0.0522 0.00942 0.00312 -0.0549 0.9431 0.0720 -2.250 0.0784 0.00946 0.00321 -0.0543 0.9362 0.0836 -2.000 0.1156 0.00931 0.00306 -0.0562 0.9330 0.0896 -1.750 0.1557 0.00920 0.00297 -0.0588 0.9302 0.0970 -1.500 0.1831 0.00913 0.00288 -0.0585 0.9224 0.1000 -1.250 0.2193 0.00885 0.00266 -0.0603 0.9169 0.1086 -1.000 0.2474 0.00868 0.00247 -0.0601 0.9063 0.1120 -0.750 0.2768 0.00851 0.00227 -0.0602 0.8945 0.1139 -0.500 0.3037 0.00823 0.00200 -0.0599 0.8811 0.1180 -0.250 0.3305 0.00808 0.00186 -0.0594 0.8665 0.1221 0.000 0.3570 0.00798 0.00173 -0.0590 0.8502 0.1266 0.250 0.3824 0.00784 0.00161 -0.0583 0.8320 0.1334 0.500 0.4076 0.00776 0.00151 -0.0576 0.8093 0.1433 0.750 0.4318 0.00764 0.00142 -0.0567 0.7816 0.1710 1.000 0.5642 0.00637 0.00212 -0.0804 0.7313 0.9922 1.250 0.6192 0.00656 0.00211 -0.0865 0.6910 1.0000 1.500 0.6386 0.00675 0.00216 -0.0847 0.6582 1.0000 1.750 0.6561 0.00700 0.00222 -0.0824 0.6100 1.0000 2.000 0.6678 0.00752 0.00232 -0.0791 0.5099 1.0000 2.250 0.6791 0.00822 0.00250 -0.0758 0.4023 1.0000 2.500 0.6973 0.00861 0.00268 -0.0740 0.3576 1.0000 2.750 0.7171 0.00892 0.00284 -0.0725 0.3279 1.0000 3.000 0.7361 0.00928 0.00301 -0.0709 0.2860 1.0000 3.250 0.7553 0.00966 0.00318 -0.0693 0.2377 1.0000 3.500 0.7711 0.01032 0.00342 -0.0672 0.1619 1.0000 3.750 0.7806 0.01160 0.00403 -0.0639 0.0352 1.0000 4.000 0.7997 0.01210 0.00450 -0.0621 0.0200 1.0000 4.250 0.8199 0.01254 0.00510 -0.0604 0.0163 1.0000 4.500 0.8400 0.01297 0.00563 -0.0587 0.0156 1.0000 4.750 0.8591 0.01353 0.00631 -0.0569 0.0149 1.0000 5.000 0.8770 0.01419 0.00708 -0.0548 0.0145 1.0000 5.250 0.8944 0.01486 0.00783 -0.0527 0.0136 1.0000 5.500 0.9111 0.01560 0.00863 -0.0506 0.0126 1.0000 5.750 0.9262 0.01650 0.00961 -0.0481 0.0118 1.0000 6.000 0.9411 0.01748 0.01068 -0.0455 0.0117 1.0000 6.250 0.9556 0.01866 0.01194 -0.0429 0.0114 1.0000 6.500 0.9718 0.02017 0.01357 -0.0404 0.0121 1.0000 6.750 1.0031 0.02322 0.01687 -0.0389 0.0241 1.0000 7.000 1.0225 0.02454 0.01837 -0.0372 0.0227 1.0000 7.250 1.0399 0.02607 0.02004 -0.0354 0.0207 1.0000 7.500 1.0569 0.02802 0.02208 -0.0338 0.0191 1.0000 7.750 1.0704 0.03089 0.02508 -0.0319 0.0176 1.0000 8.000 1.0641 0.03852 0.03324 -0.0275 0.0162 1.0000 8.250 1.0704 0.03923 0.03422 -0.0239 0.0160 1.0000 8.500 1.0871 0.03746 0.03257 -0.0214 0.0143 1.0000 8.750 1.0954 0.03839 0.03366 -0.0185 0.0126 1.0000 9.000 1.0975 0.04055 0.03603 -0.0150 0.0120 1.0000 9.250 1.0973 0.04268 0.03834 -0.0115 0.0115 1.0000 9.500 1.0936 0.04503 0.04089 -0.0076 0.0113 1.0000 9.750 1.0865 0.04708 0.04307 -0.0034 0.0109 1.0000 10.000 1.0752 0.04938 0.04551 0.0011 0.0107 1.0000 10.250 1.0693 0.05185 0.04806 0.0040 0.0104 1.0000 10.500 1.0579 0.05458 0.05093 0.0070 0.0103 1.0000 10.750 1.0435 0.05786 0.05436 0.0093 0.0100 1.0000 11.000 1.0269 0.06122 0.05789 0.0109 0.0100 1.0000 11.250 1.0101 0.06511 0.06192 0.0113 0.0099 1.0000 11.500 0.9922 0.06954 0.06650 0.0104 0.0099 1.0000 11.750 0.9660 0.07560 0.07280 0.0068 0.0105 1.0000 12.000 0.9480 0.08210 0.07943 0.0027 0.0104 1.0000 12.250 0.9233 0.09166 0.08918 -0.0046 0.0107 1.0000 12.500 0.8860 0.10735 0.10509 -0.0158 0.0114 1.0000