XFOIL Version 6.96 Calculated polar for: FX 73-K-170/22 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 ------ -------- --------- --------- -------- -------- -------- -10.500 -0.0315 0.04051 0.03719 -0.1563 0.7989 0.0290 -10.250 -0.0605 0.03483 0.03144 -0.1592 0.7969 0.0289 -10.000 -0.0850 0.03076 0.02728 -0.1605 0.7943 0.0289 -9.750 -0.1057 0.02763 0.02405 -0.1607 0.7915 0.0289 -9.500 -0.1300 0.02552 0.02177 -0.1595 0.7886 0.0296 -9.250 -0.1538 0.02570 0.02173 -0.1552 0.7858 0.0304 -9.000 -0.2459 0.02583 0.02015 -0.1544 0.7870 0.0155 -8.750 -0.2272 0.02537 0.01951 -0.1534 0.7851 0.0153 -8.500 -0.2098 0.02373 0.01770 -0.1525 0.7831 0.0151 -8.250 -0.1949 0.02226 0.01605 -0.1509 0.7809 0.0153 -8.000 -0.1768 0.02044 0.01409 -0.1498 0.7785 0.0154 -7.750 -0.1565 0.01941 0.01297 -0.1489 0.7761 0.0155 -7.500 -0.1370 0.01827 0.01181 -0.1480 0.7738 0.0162 -7.250 -0.1159 0.01753 0.01099 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0.8479 0.01047 0.00489 -0.1336 0.6770 0.6893 2.750 0.8711 0.01051 0.00496 -0.1328 0.6734 0.6919 3.000 0.8970 0.01052 0.00496 -0.1327 0.6700 0.6945 3.250 0.9247 0.01049 0.00494 -0.1328 0.6671 0.6970 3.500 0.9546 0.01052 0.00495 -0.1335 0.6643 0.6994 3.750 0.9745 0.01057 0.00510 -0.1321 0.6604 0.7018 4.000 0.9983 0.01060 0.00516 -0.1315 0.6566 0.7045 4.250 1.0248 0.01062 0.00518 -0.1314 0.6531 0.7074 4.500 1.0547 0.01068 0.00521 -0.1321 0.6498 0.7103 4.750 1.0732 0.01073 0.00535 -0.1305 0.6455 0.7128 5.000 1.0959 0.01075 0.00543 -0.1296 0.6410 0.7154 5.250 1.1220 0.01079 0.00549 -0.1295 0.6373 0.7183 5.500 1.1471 0.01087 0.00559 -0.1292 0.6331 0.7213 5.750 1.1646 0.01093 0.00573 -0.1273 0.6276 0.7248 6.000 1.1882 0.01096 0.00576 -0.1267 0.6225 0.7277 6.250 1.2091 0.01102 0.00589 -0.1255 0.6169 0.7306 6.500 1.2252 0.01108 0.00602 -0.1233 0.6105 0.7338 6.750 1.2505 0.01115 0.00608 -0.1231 0.6047 0.7375 7.000 1.2568 0.01124 0.00626 -0.1189 0.5973 0.7415 7.250 1.2756 0.01130 0.00632 -0.1173 0.5896 0.7453 7.500 1.2850 0.01148 0.00662 -0.1139 0.5821 0.7493 7.750 1.2948 0.01169 0.00684 -0.1107 0.5705 0.7540 8.000 1.3043 0.01199 0.00715 -0.1075 0.5573 0.7587 8.250 1.3164 0.01235 0.00756 -0.1052 0.5442 0.7638 8.500 1.3276 0.01285 0.00809 -0.1029 0.5297 0.7702 8.750 1.3398 0.01349 0.00877 -0.1012 0.5130 0.7766 9.000 1.3532 0.01426 0.00957 -0.0999 0.4951 0.7840 9.250 1.3658 0.01523 0.01053 -0.0988 0.4751 0.7924 9.500 1.3771 0.01643 0.01172 -0.0979 0.4527 0.8034 9.750 1.3853 0.01807 0.01332 -0.0970 0.4217 0.8176 10.000 1.3905 0.02023 0.01540 -0.0964 0.3831 0.8393 10.250 1.4110 0.02271 0.01786 -0.0996 0.3411 0.8921 10.500 1.4168 0.02568 0.02064 -0.0999 0.2964 1.0000 10.750 1.4131 0.02785 0.02267 -0.0973 0.2680 1.0000 11.000 1.4072 0.03027 0.02491 -0.0946 0.2359 1.0000 11.250 1.3981 0.03301 0.02743 -0.0917 0.2006 1.0000 11.500 1.3938 0.03550 0.02974 -0.0895 0.1703 1.0000 11.750 1.3923 0.03783 0.03195 -0.0875 0.1453 1.0000 12.000 1.3871 0.04053 0.03446 -0.0854 0.1166 1.0000 12.250 1.3860 0.04295 0.03675 -0.0837 0.0933 1.0000 12.500 1.3858 0.04537 0.03908 -0.0822 0.0762 1.0000 12.750 1.3858 0.04782 0.04145 -0.0807 0.0600 1.0000 13.000 1.3876 0.05016 0.04373 -0.0795 0.0492 1.0000 13.250 1.3894 0.05254 0.04607 -0.0783 0.0405 1.0000 13.500 1.3914 0.05494 0.04848 -0.0772 0.0358 1.0000 13.750 1.3976 0.05699 0.05059 -0.0765 0.0322 1.0000 14.000 1.4002 0.05943 0.05304 -0.0756 0.0291 1.0000 14.250 1.4051 0.06168 0.05535 -0.0749 0.0265 1.0000 14.500 1.4092 0.06399 0.05771 -0.0742 0.0244 1.0000 14.750 1.4068 0.06709 0.06084 -0.0733 0.0221 1.0000 15.000 1.4131 0.06925 0.06309 -0.0728 0.0202 1.0000 15.250 1.4157 0.07187 0.06577 -0.0723 0.0190 1.0000 15.500 1.4105 0.07544 0.06938 -0.0716 0.0170 1.0000 15.750 1.4144 0.07796 0.07200 -0.0712 0.0160 1.0000 16.000 1.4168 0.08070 0.07481 -0.0709 0.0148 1.0000 16.250 1.4146 0.08401 0.07816 -0.0706 0.0137 1.0000 16.500 1.4099 0.08772 0.08197 -0.0704 0.0131 1.0000 16.750 1.4111 0.09074 0.08509 -0.0703 0.0124 1.0000 17.000 1.4123 0.09376 0.08820 -0.0703 0.0118 1.0000 17.250 1.4112 0.09712 0.09163 -0.0704 0.0112 1.0000 17.500 1.4087 0.10068 0.09525 -0.0706 0.0107 1.0000 17.750 1.4041 0.10457 0.09921 -0.0709 0.0104 1.0000