XFOIL Version 6.96 Calculated polar for: St. CYR 171 (Royer) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.500 -0.6576 0.10002 0.09182 -0.0137 1.0000 0.0815 -11.250 -0.6757 0.09213 0.08399 -0.0176 1.0000 0.0827 -10.750 -0.8505 0.05774 0.04926 -0.0378 1.0000 0.0776 -10.500 -0.8546 0.05555 0.04705 -0.0362 1.0000 0.0791 -10.250 -0.8605 0.05285 0.04425 -0.0347 1.0000 0.0808 -10.000 -0.8649 0.04999 0.04121 -0.0332 1.0000 0.0831 -9.750 -0.8673 0.04694 0.03787 -0.0315 1.0000 0.0859 -9.500 -0.8668 0.04371 0.03421 -0.0296 1.0000 0.0892 -9.250 -0.8547 0.04237 0.03294 -0.0279 1.0000 0.0923 -9.000 -0.8437 0.04080 0.03128 -0.0261 1.0000 0.0967 -8.750 -0.8345 0.03850 0.02859 -0.0241 1.0000 0.1035 -8.500 -0.8209 0.03752 0.02773 -0.0222 1.0000 0.1097 -8.250 -0.8085 0.03598 0.02596 -0.0203 1.0000 0.1204 -8.000 -0.7941 0.03513 0.02506 -0.0186 1.0000 0.1317 -7.750 -0.7790 0.03430 0.02417 -0.0168 1.0000 0.1427 -7.500 -0.7633 0.03328 0.02285 -0.0152 1.0000 0.1544 -7.250 -0.7464 0.03278 0.02236 -0.0135 1.0000 0.1650 -7.000 -0.7292 0.03208 0.02155 -0.0119 1.0000 0.1754 -6.750 -0.7117 0.03148 0.02076 -0.0104 1.0000 0.1870 -6.500 -0.6938 0.03102 0.02033 -0.0088 1.0000 0.1974 -6.250 -0.6756 0.03037 0.01949 -0.0073 1.0000 0.2087 -6.000 -0.6568 0.02975 0.01881 -0.0058 1.0000 0.2181 -5.750 -0.6376 0.02901 0.01795 -0.0044 1.0000 0.2268 -5.500 -0.6181 0.02828 0.01717 -0.0029 1.0000 0.2347 -5.250 -0.5976 0.02754 0.01624 -0.0016 1.0000 0.2417 -5.000 -0.5777 0.02683 0.01555 -0.0001 1.0000 0.2477 -4.750 -0.5570 0.02620 0.01481 0.0013 1.0000 0.2547 -4.500 -0.5371 0.02558 0.01419 0.0028 1.0000 0.2618 -4.250 -0.5173 0.02500 0.01358 0.0043 1.0000 0.2712 -4.000 -0.4981 0.02446 0.01310 0.0059 1.0000 0.2806 -3.750 -0.4785 0.02398 0.01264 0.0075 1.0000 0.2917 -3.500 -0.4605 0.02364 0.01249 0.0094 1.0000 0.3021 -3.250 -0.4427 0.02352 0.01260 0.0115 1.0000 0.3137 -3.000 -0.4254 0.02373 0.01314 0.0137 1.0000 0.3267 -2.750 -0.4076 0.02419 0.01391 0.0161 1.0000 0.3404 -2.250 -0.3696 0.02672 0.01588 0.0196 1.0000 0.4281 -2.000 -0.3533 0.02732 0.01629 0.0216 1.0000 0.4457 -1.750 -0.3375 0.02734 0.01618 0.0235 1.0000 0.4604 -1.500 -0.3223 0.02707 0.01577 0.0254 1.0000 0.4748 -1.250 -0.3072 0.02663 0.01520 0.0271 1.0000 0.4884 -1.000 -0.2738 0.02590 0.01433 0.0251 0.9901 0.5051 -0.750 -0.2371 0.02505 0.01336 0.0225 0.9783 0.5208 -0.500 -0.1991 0.02414 0.01237 0.0198 0.9666 0.5349 -0.250 -0.1626 0.02342 0.01160 0.0175 0.9536 0.5467 0.000 -0.1231 0.02259 0.01080 0.0148 0.9412 0.5579 0.250 -0.0770 0.02201 0.01031 0.0110 0.9292 0.5673 0.500 -0.0237 0.02145 0.00987 0.0063 0.9100 0.5749 0.750 0.0372 0.02077 0.00935 0.0011 0.8810 0.5804 1.000 0.0882 0.02022 0.00892 -0.0020 0.8465 0.5839 1.250 0.1328 0.01986 0.00867 -0.0041 0.8163 0.5869 1.500 0.1706 0.01961 0.00852 -0.0050 0.7850 0.5903 1.750 0.2057 0.01941 0.00842 -0.0054 0.7512 0.5936 2.000 0.2366 0.01927 0.00838 -0.0050 0.7145 0.5974 2.250 0.2630 0.01923 0.00841 -0.0038 0.6722 0.6010 2.500 0.2867 0.01926 0.00850 -0.0022 0.6233 0.6039 2.750 0.3097 0.01939 0.00852 -0.0003 0.5643 0.6060 3.000 0.3316 0.01972 0.00859 0.0015 0.5001 0.6071 3.250 0.3527 0.02021 0.00882 0.0032 0.4326 0.6069 3.500 0.3745 0.02086 0.00907 0.0045 0.3773 0.6053 3.750 0.3974 0.02160 0.00944 0.0054 0.3421 0.6034 4.000 0.4219 0.02233 0.00996 0.0060 0.3181 0.6016 4.250 0.4474 0.02307 0.01056 0.0064 0.3011 0.6000 4.500 0.4736 0.02383 0.01119 0.0067 0.2870 0.5985 4.750 0.5003 0.02453 0.01191 0.0070 0.2736 0.5971 5.000 0.5269 0.02529 0.01265 0.0073 0.2631 0.5958 5.250 0.5540 0.02606 0.01346 0.0075 0.2542 0.5947 5.500 0.5811 0.02692 0.01427 0.0077 0.2468 0.5935 5.750 0.6068 0.02772 0.01527 0.0082 0.2381 0.5925 6.000 0.6327 0.02860 0.01612 0.0085 0.2304 0.5915 6.250 0.6580 0.02957 0.01728 0.0090 0.2236 0.5905 6.500 0.6820 0.03048 0.01836 0.0097 0.2155 0.5896 6.750 0.7041 0.03133 0.01930 0.0105 0.2051 0.5888 7.000 0.7244 0.03191 0.01987 0.0116 0.1923 0.5879 7.250 0.7420 0.03250 0.02068 0.0130 0.1782 0.5870 7.500 0.7598 0.03308 0.02137 0.0144 0.1652 0.5862 7.750 0.7791 0.03369 0.02196 0.0155 0.1549 0.5854 8.000 0.7968 0.03482 0.02348 0.0169 0.1437 0.5846 8.250 0.8144 0.03581 0.02455 0.0182 0.1339 0.5838 8.500 0.8302 0.03688 0.02579 0.0198 0.1229 0.5830 8.750 0.8444 0.03837 0.02751 0.0213 0.1126 0.5823 9.000 0.8596 0.03920 0.02828 0.0228 0.1054 0.5816 9.250 0.8710 0.04145 0.03094 0.0244 0.0984 0.5809 9.500 0.8832 0.04315 0.03280 0.0260 0.0938 0.5802 9.750 0.8973 0.04444 0.03405 0.0274 0.0906 0.5795 10.000 0.8996 0.04759 0.03764 0.0293 0.0876 0.5789 10.250 0.8972 0.05074 0.04115 0.0313 0.0851 0.5783 10.500 0.8920 0.05368 0.04436 0.0332 0.0829 0.5777 10.750 0.8829 0.05646 0.04733 0.0354 0.0814 0.5771 11.000 0.8783 0.05874 0.04970 0.0370 0.0795 0.5764 11.250 0.8753 0.06112 0.05213 0.0380 0.0781 0.5758 11.500 0.8650 0.06451 0.05558 0.0382 0.0771 0.5753 11.750 0.8323 0.07111 0.06238 0.0357 0.0772 0.5748