XFOIL Version 6.96 Calculated polar for: NPL 9627 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.9077 0.13117 0.12818 0.0098 1.0000 0.0096 -16.750 -0.9519 0.11692 0.11375 0.0022 1.0000 0.0095 -16.500 -0.9848 0.10581 0.10248 -0.0039 1.0000 0.0094 -16.250 -1.0135 0.09607 0.09259 -0.0093 1.0000 0.0094 -16.000 -1.0399 0.08723 0.08360 -0.0142 1.0000 0.0093 -15.750 -1.0641 0.07903 0.07525 -0.0188 1.0000 0.0093 -15.500 -1.0853 0.07148 0.06755 -0.0232 1.0000 0.0093 -15.250 -1.1032 0.06450 0.06042 -0.0274 1.0000 0.0093 -15.000 -1.1178 0.05809 0.05384 -0.0314 1.0000 0.0093 -14.750 -1.1288 0.05238 0.04797 -0.0351 1.0000 0.0093 -14.500 -1.1369 0.04746 0.04288 -0.0381 1.0000 0.0093 -14.250 -1.1425 0.04331 0.03857 -0.0403 1.0000 0.0093 -14.000 -1.1462 0.03984 0.03494 -0.0415 1.0000 0.0094 -13.750 -1.1478 0.03698 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0.0396 -4.000 -0.3353 0.01036 0.00329 -0.0184 0.8874 0.0479 -3.750 -0.3103 0.00992 0.00299 -0.0178 0.8717 0.0830 -3.500 -0.2857 0.00945 0.00273 -0.0172 0.8547 0.1386 -3.250 -0.2606 0.00910 0.00252 -0.0166 0.8364 0.1851 -3.000 -0.2349 0.00884 0.00235 -0.0161 0.8176 0.2249 -2.500 -0.1827 0.00847 0.00210 -0.0153 0.7790 0.2931 -2.250 -0.1567 0.00834 0.00200 -0.0148 0.7555 0.3255 -2.000 -0.1304 0.00824 0.00193 -0.0144 0.7319 0.3596 -1.750 -0.1039 0.00815 0.00186 -0.0141 0.7110 0.3891 -1.500 -0.0771 0.00808 0.00179 -0.0137 0.6920 0.4150 -1.250 -0.0505 0.00799 0.00173 -0.0134 0.6724 0.4417 -0.750 0.0023 0.00783 0.00163 -0.0127 0.6302 0.5055 -0.500 0.0285 0.00771 0.00160 -0.0123 0.6129 0.5448 -0.250 0.0545 0.00759 0.00159 -0.0118 0.5955 0.5927 0.000 0.0802 0.00749 0.00159 -0.0113 0.5754 0.6409 0.250 0.1061 0.00743 0.00160 -0.0108 0.5554 0.6854 0.500 0.1322 0.00738 0.00163 -0.0102 0.5386 0.7251 0.750 0.1584 0.00735 0.00167 -0.0097 0.5246 0.7614 1.000 0.1847 0.00736 0.00172 -0.0092 0.5078 0.7942 1.250 0.2109 0.00739 0.00179 -0.0086 0.4875 0.8223 1.500 0.2374 0.00746 0.00185 -0.0081 0.4658 0.8475 1.750 0.2637 0.00758 0.00193 -0.0076 0.4415 0.8687 2.000 0.2904 0.00771 0.00202 -0.0071 0.4191 0.8878 2.250 0.3174 0.00788 0.00211 -0.0068 0.3933 0.9042 2.500 0.3446 0.00807 0.00222 -0.0065 0.3659 0.9190 2.750 0.3728 0.00829 0.00234 -0.0065 0.3386 0.9315 3.000 0.4017 0.00856 0.00248 -0.0067 0.3064 0.9420 3.250 0.4301 0.00884 0.00263 -0.0069 0.2762 0.9522 3.500 0.4614 0.00913 0.00281 -0.0076 0.2497 0.9601 3.750 0.4919 0.00942 0.00298 -0.0083 0.2240 0.9683 4.000 0.5243 0.00977 0.00319 -0.0094 0.1913 0.9749 4.250 0.5551 0.01023 0.00344 -0.0102 0.1517 0.9814 4.500 0.5893 0.01072 0.00374 -0.0119 0.1137 0.9851 4.750 0.6223 0.01111 0.00401 -0.0132 0.0942 0.9891 5.000 0.6546 0.01142 0.00427 -0.0144 0.0857 0.9929 5.250 0.6884 0.01174 0.00453 -0.0158 0.0799 0.9952 5.500 0.7223 0.01199 0.00478 -0.0172 0.0768 0.9979 5.750 0.7537 0.01227 0.00505 -0.0182 0.0737 1.0000 6.000 0.7751 0.01256 0.00532 -0.0170 0.0713 1.0000 6.250 0.7969 0.01280 0.00558 -0.0159 0.0698 1.0000 6.500 0.8190 0.01304 0.00583 -0.0148 0.0685 1.0000 6.750 0.8410 0.01329 0.00611 -0.0137 0.0670 1.0000 7.000 0.8629 0.01357 0.00640 -0.0126 0.0654 1.0000 7.250 0.8845 0.01390 0.00672 -0.0115 0.0637 1.0000 7.500 0.9055 0.01428 0.00711 -0.0103 0.0620 1.0000 7.750 0.9281 0.01453 0.00740 -0.0094 0.0608 1.0000 8.000 0.9507 0.01481 0.00771 -0.0085 0.0592 1.0000 8.250 0.9733 0.01512 0.00804 -0.0076 0.0575 1.0000 8.500 0.9954 0.01547 0.00840 -0.0067 0.0558 1.0000 8.750 1.0176 0.01585 0.00879 -0.0058 0.0541 1.0000 9.000 1.0408 0.01614 0.00914 -0.0051 0.0523 1.0000 9.250 1.0637 0.01647 0.00949 -0.0044 0.0502 1.0000 9.500 1.0860 0.01685 0.00987 -0.0036 0.0483 1.0000 9.750 1.1086 0.01720 0.01028 -0.0029 0.0462 1.0000 10.000 1.1310 0.01757 0.01067 -0.0021 0.0441 1.0000 10.250 1.1526 0.01799 0.01109 -0.0013 0.0422 1.0000 10.500 1.1741 0.01841 0.01157 -0.0004 0.0403 1.0000 10.750 1.1951 0.01886 0.01203 0.0004 0.0383 1.0000 11.000 1.2151 0.01938 0.01257 0.0014 0.0369 1.0000 11.250 1.2345 0.01991 0.01316 0.0025 0.0357 1.0000 11.500 1.2532 0.02048 0.01377 0.0036 0.0346 1.0000 11.750 1.2708 0.02109 0.01441 0.0049 0.0337 1.0000 12.000 1.2863 0.02178 0.01513 0.0064 0.0328 1.0000 12.250 1.3003 0.02243 0.01587 0.0082 0.0322 1.0000 12.500 1.3136 0.02315 0.01665 0.0099 0.0315 1.0000 12.750 1.3264 0.02393 0.01750 0.0116 0.0307 1.0000 13.000 1.3382 0.02481 0.01844 0.0132 0.0299 1.0000 13.250 1.3485 0.02583 0.01951 0.0147 0.0292 1.0000 13.500 1.3575 0.02700 0.02074 0.0162 0.0286 1.0000 13.750 1.3679 0.02813 0.02197 0.0174 0.0280 1.0000 14.000 1.3773 0.02940 0.02334 0.0184 0.0274 1.0000 14.250 1.3857 0.03083 0.02486 0.0193 0.0268 1.0000 14.500 1.3927 0.03246 0.02658 0.0199 0.0263 1.0000 14.750 1.3982 0.03433 0.02853 0.0204 0.0259 1.0000 15.000 1.4020 0.03649 0.03077 0.0205 0.0254 1.0000 15.250 1.4034 0.03902 0.03339 0.0204 0.0250 1.0000 15.500 1.4056 0.04159 0.03607 0.0201 0.0247 1.0000 15.750 1.4076 0.04426 0.03887 0.0196 0.0244 1.0000 16.000 1.4082 0.04721 0.04193 0.0189 0.0241 1.0000 16.250 1.4068 0.05048 0.04533 0.0180 0.0237 1.0000 16.500 1.4037 0.05403 0.04900 0.0168 0.0234 1.0000 16.750 1.3988 0.05792 0.05301 0.0155 0.0231 1.0000 17.000 1.3920 0.06211 0.05732 0.0139 0.0229 1.0000 17.250 1.3833 0.06669 0.06201 0.0121 0.0226 1.0000 17.500 1.3728 0.07168 0.06712 0.0099 0.0224 1.0000 17.750 1.3607 0.07701 0.07256 0.0076 0.0222 1.0000 18.000 1.3467 0.08278 0.07845 0.0050 0.0220 1.0000 18.250 1.3315 0.08888 0.08467 0.0021 0.0219 1.0000 18.500 1.3148 0.09531 0.09121 -0.0010 0.0217 1.0000 18.750 1.2977 0.10196 0.09797 -0.0042 0.0216 1.0000