XFOIL Version 6.96 Calculated polar for: S4320 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 ------ -------- --------- --------- -------- -------- -------- -10.750 -0.3319 0.11713 0.11546 -0.0224 1.0000 0.0039 -10.500 -0.3270 0.11368 0.11202 -0.0236 1.0000 0.0038 -8.000 -0.4042 0.02051 0.01698 -0.0918 0.7822 0.0060 -7.750 -0.3819 0.01765 0.01363 -0.0925 0.7735 0.0065 -7.500 -0.3566 0.01626 0.01195 -0.0927 0.7651 0.0067 -7.250 -0.3306 0.01511 0.01057 -0.0929 0.7567 0.0070 -7.000 -0.3036 0.01458 0.00992 -0.0930 0.7486 0.0073 -6.750 -0.2761 0.01429 0.00956 -0.0930 0.7406 0.0075 -6.500 -0.2486 0.01400 0.00917 -0.0930 0.7330 0.0077 -6.250 -0.2210 0.01358 0.00865 -0.0930 0.7253 0.0080 -6.000 -0.1935 0.01308 0.00801 -0.0931 0.7182 0.0084 -5.750 -0.1659 0.01252 0.00730 -0.0931 0.7108 0.0088 -5.500 -0.1382 0.01203 0.00667 -0.0931 0.7041 0.0092 -5.250 -0.1102 0.01170 0.00623 -0.0931 0.6970 0.0096 -5.000 -0.0824 0.01119 0.00560 -0.0931 0.6906 0.0100 -4.750 -0.0544 0.01081 0.00516 -0.0932 0.6837 0.0104 -4.500 -0.0264 0.01054 0.00482 -0.0932 0.6773 0.0108 -4.250 0.0018 0.01023 0.00444 -0.0932 0.6707 0.0111 -4.000 0.0300 0.00993 0.00407 -0.0932 0.6642 0.0116 -3.750 0.0583 0.00963 0.00370 -0.0932 0.6579 0.0121 -3.500 0.0866 0.00942 0.00343 -0.0932 0.6512 0.0127 -3.250 0.1150 0.00924 0.00319 -0.0932 0.6450 0.0131 -3.000 0.1434 0.00905 0.00293 -0.0933 0.6380 0.0134 -2.750 0.1717 0.00869 0.00250 -0.0933 0.6318 0.0138 -2.500 0.2002 0.00842 0.00218 -0.0933 0.6247 0.0144 -2.250 0.2286 0.00825 0.00195 -0.0934 0.6180 0.0150 -2.000 0.2571 0.00811 0.00177 -0.0934 0.6107 0.0156 -1.750 0.2855 0.00801 0.00163 -0.0934 0.6035 0.0165 -1.500 0.3141 0.00791 0.00149 -0.0934 0.5955 0.0173 -1.250 0.3425 0.00784 0.00137 -0.0934 0.5876 0.0179 -1.000 0.3710 0.00778 0.00126 -0.0935 0.5790 0.0186 -0.750 0.3994 0.00773 0.00117 -0.0935 0.5708 0.0205 -0.500 0.4278 0.00769 0.00110 -0.0935 0.5618 0.0237 -0.250 0.4562 0.00756 0.00105 -0.0936 0.5530 0.0582 0.000 0.4845 0.00740 0.00103 -0.0937 0.5444 0.1181 0.250 0.5127 0.00729 0.00103 -0.0938 0.5349 0.1720 0.500 0.5410 0.00718 0.00104 -0.0939 0.5255 0.2339 0.750 0.5690 0.00704 0.00108 -0.0941 0.5153 0.3173 1.000 0.5970 0.00690 0.00113 -0.0942 0.5039 0.4114 1.250 0.6244 0.00658 0.00122 -0.0944 0.4920 0.5906 1.500 0.6510 0.00632 0.00133 -0.0941 0.4794 0.7426 1.750 0.6749 0.00612 0.00141 -0.0932 0.4667 0.8655 2.000 0.7035 0.00603 0.00144 -0.0931 0.4532 1.0000 2.250 0.7313 0.00618 0.00150 -0.0931 0.4390 1.0000 2.500 0.7590 0.00634 0.00158 -0.0931 0.4239 1.0000 2.750 0.7865 0.00652 0.00167 -0.0930 0.4082 1.0000 3.000 0.8140 0.00670 0.00177 -0.0930 0.3926 1.0000 3.250 0.8413 0.00689 0.00188 -0.0929 0.3769 1.0000 3.500 0.8684 0.00711 0.00202 -0.0928 0.3594 1.0000 3.750 0.8955 0.00733 0.00215 -0.0928 0.3427 1.0000 4.000 0.9225 0.00755 0.00230 -0.0927 0.3261 1.0000 4.250 0.9493 0.00778 0.00245 -0.0926 0.3106 1.0000 4.500 0.9760 0.00802 0.00263 -0.0924 0.2941 1.0000 4.750 1.0026 0.00827 0.00280 -0.0923 0.2788 1.0000 5.000 1.0290 0.00853 0.00299 -0.0922 0.2634 1.0000 5.250 1.0554 0.00878 0.00318 -0.0920 0.2501 1.0000 5.500 1.0816 0.00906 0.00340 -0.0918 0.2358 1.0000 5.750 1.1076 0.00934 0.00362 -0.0917 0.2219 1.0000 6.000 1.1334 0.00963 0.00386 -0.0914 0.2080 1.0000 6.250 1.1593 0.00991 0.00409 -0.0912 0.1969 1.0000 6.500 1.1849 0.01021 0.00435 -0.0910 0.1856 1.0000 6.750 1.2101 0.01054 0.00463 -0.0907 0.1731 1.0000 7.000 1.2351 0.01087 0.00491 -0.0904 0.1615 1.0000 7.500 1.2836 0.01167 0.00559 -0.0896 0.1332 1.0000 7.750 1.3075 0.01207 0.00593 -0.0892 0.1213 1.0000 8.000 1.3310 0.01250 0.00631 -0.0887 0.1088 1.0000 8.250 1.3534 0.01302 0.00674 -0.0880 0.0938 1.0000 8.500 1.3756 0.01353 0.00720 -0.0874 0.0807 1.0000 8.750 1.3976 0.01404 0.00766 -0.0867 0.0708 1.0000 9.000 1.4190 0.01457 0.00815 -0.0859 0.0609 1.0000 9.250 1.4400 0.01511 0.00865 -0.0851 0.0519 1.0000 9.500 1.4601 0.01570 0.00921 -0.0842 0.0430 1.0000 9.750 1.4771 0.01650 0.00993 -0.0829 0.0309 1.0000 10.000 1.4930 0.01734 0.01070 -0.0814 0.0201 1.0000 10.250 1.5024 0.01858 0.01185 -0.0790 0.0067 1.0000 10.500 1.5168 0.01933 0.01263 -0.0772 0.0045 1.0000 10.750 1.5290 0.01999 0.01334 -0.0750 0.0040 1.0000 11.000 1.5393 0.02072 0.01412 -0.0727 0.0034 1.0000 11.250 1.5497 0.02148 0.01496 -0.0705 0.0032 1.0000 11.500 1.5601 0.02231 0.01585 -0.0685 0.0030 1.0000 11.750 1.5700 0.02322 0.01683 -0.0666 0.0028 1.0000 12.000 1.5788 0.02427 0.01795 -0.0648 0.0026 1.0000 12.250 1.5871 0.02543 0.01917 -0.0631 0.0025 1.0000 12.500 1.5940 0.02676 0.02058 -0.0615 0.0023 1.0000 12.750 1.5999 0.02826 0.02216 -0.0599 0.0021 1.0000 13.000 1.6048 0.02992 0.02391 -0.0585 0.0020 1.0000 13.250 1.6097 0.03167 0.02574 -0.0573 0.0019 1.0000 13.500 1.6147 0.03348 0.02765 -0.0563 0.0019 1.0000 13.750 1.6199 0.03534 0.02960 -0.0554 0.0019 1.0000 14.000 1.6233 0.03746 0.03181 -0.0547 0.0018 1.0000 14.250 1.6267 0.03965 0.03408 -0.0541 0.0017 1.0000 14.500 1.6281 0.04214 0.03667 -0.0536 0.0017 1.0000 14.750 1.6287 0.04481 0.03944 -0.0533 0.0017 1.0000 15.000 1.6279 0.04774 0.04247 -0.0532 0.0016 1.0000 15.250 1.6255 0.05096 0.04580 -0.0533 0.0016 1.0000 15.500 1.6239 0.05421 0.04915 -0.0535 0.0015 1.0000 15.750 1.6209 0.05779 0.05284 -0.0540 0.0015 1.0000 16.000 1.6152 0.06190 0.05706 -0.0548 0.0014 1.0000 16.250 1.6112 0.06589 0.06116 -0.0558 0.0014 1.0000 16.500 1.6041 0.07053 0.06593 -0.0571 0.0014 1.0000 16.750 1.5956 0.07556 0.07109 -0.0587 0.0014 1.0000 17.000 1.5880 0.08059 0.07623 -0.0605 0.0013 1.0000 17.250 1.5776 0.08628 0.08205 -0.0627 0.0013 1.0000 17.500 1.5662 0.09232 0.08821 -0.0652 0.0013 1.0000 17.750 1.5513 0.09916 0.09519 -0.0682 0.0013 1.0000 18.000 1.5376 0.10598 0.10215 -0.0713 0.0013 1.0000 18.250 1.5243 0.11286 0.10915 -0.0746 0.0012 1.0000 18.500 1.5085 0.12037 0.11680 -0.0784 0.0012 1.0000 18.750 1.4931 0.12796 0.12452 -0.0824 0.0012 1.0000