XFOIL Version 6.96 Calculated polar for: TH 25816 HALE AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -19.750 -0.3244 0.07344 0.06986 -0.2284 0.9506 0.0143 -19.500 -0.3981 0.07341 0.06977 -0.2121 0.9428 0.0141 -19.250 -0.4029 0.07017 0.06645 -0.2132 0.9419 0.0142 -19.000 -0.4045 0.06691 0.06310 -0.2149 0.9412 0.0143 -18.750 -0.4103 0.06304 0.05907 -0.2166 0.9407 0.0143 -18.500 -0.4057 0.06016 0.05610 -0.2186 0.9404 0.0144 -18.250 -0.4033 0.05715 0.05297 -0.2203 0.9400 0.0144 -18.000 -0.3909 0.05498 0.05076 -0.2227 0.9396 0.0146 -17.750 -0.3851 0.05223 0.04787 -0.2244 0.9393 0.0145 -17.500 -0.3754 0.04983 0.04537 -0.2261 0.9391 0.0146 -17.250 -0.3604 0.04794 0.04341 -0.2283 0.9388 0.0147 -17.000 -0.3464 0.04600 0.04139 -0.2301 0.9386 0.0148 -16.750 -0.3315 0.04424 0.03955 -0.2317 0.9383 0.0149 -16.500 -0.3153 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3.000 0.6018 0.00975 0.00520 -0.0831 0.6776 0.7591 3.250 0.6154 0.00994 0.00544 -0.0808 0.6754 0.7627 3.500 0.6316 0.01011 0.00564 -0.0791 0.6729 0.7664 3.750 0.6523 0.01025 0.00578 -0.0783 0.6704 0.7698 4.000 0.6741 0.01036 0.00590 -0.0777 0.6678 0.7730 4.250 0.6975 0.01045 0.00602 -0.0774 0.6654 0.7762 4.500 0.7269 0.01050 0.00607 -0.0784 0.6628 0.7791 4.750 0.7558 0.01059 0.00614 -0.0793 0.6602 0.7822 5.000 0.7640 0.01089 0.00649 -0.0761 0.6571 0.7861 5.250 0.7801 0.01110 0.00673 -0.0744 0.6538 0.7895 5.500 0.7984 0.01128 0.00694 -0.0732 0.6506 0.7930 5.750 0.8227 0.01140 0.00706 -0.0731 0.6475 0.7960 6.000 0.8555 0.01142 0.00706 -0.0748 0.6442 0.7988 6.250 0.8617 0.01183 0.00752 -0.0713 0.6410 0.8026 6.500 0.8749 0.01215 0.00787 -0.0692 0.6371 0.8056 6.750 0.8914 0.01239 0.00814 -0.0676 0.6329 0.8089 7.000 0.9171 0.01249 0.00823 -0.0679 0.6292 0.8115 7.250 0.9302 0.01286 0.00865 -0.0658 0.6252 0.8147 7.500 0.9401 0.01331 0.00915 -0.0631 0.6206 0.8182 7.750 0.9568 0.01363 0.00946 -0.0618 0.6161 0.8212 8.000 0.9819 0.01375 0.00954 -0.0620 0.6114 0.8234 8.250 0.9842 0.01442 0.01030 -0.0580 0.6060 0.8268 8.500 0.9965 0.01488 0.01079 -0.0559 0.6000 0.8293 8.750 1.0084 0.01536 0.01127 -0.0537 0.5931 0.8320 9.000 1.0188 0.01595 0.01190 -0.0514 0.5871 0.8349 9.250 1.0316 0.01645 0.01239 -0.0495 0.5802 0.8377 9.500 1.0392 0.01718 0.01314 -0.0468 0.5719 0.8401 9.750 1.0474 0.01784 0.01378 -0.0442 0.5628 0.8429 10.000 1.0567 0.01854 0.01453 -0.0419 0.5550 0.8452 10.250 1.0648 0.01928 0.01527 -0.0394 0.5461 0.8475 10.500 1.0714 0.02014 0.01615 -0.0367 0.5353 0.8499 10.750 1.0757 0.02110 0.01709 -0.0338 0.5229 0.8525 11.000 1.0770 0.02223 0.01819 -0.0304 0.5101 0.8550 11.250 1.0777 0.02344 0.01935 -0.0271 0.4945 0.8571 11.500 1.0740 0.02484 0.02070 -0.0232 0.4773 0.8594 11.750 1.0686 0.02636 0.02218 -0.0192 0.4578 0.8616 12.000 1.0663 0.02779 0.02357 -0.0157 0.4403 0.8636 12.250 1.0626 0.02937 0.02509 -0.0122 0.4231 0.8655 12.500 1.0616 0.03086 0.02653 -0.0091 0.4054 0.8676 12.750 1.0589 0.03249 0.02812 -0.0060 0.3883 0.8697 13.000 1.0587 0.03403 0.02960 -0.0033 0.3708 0.8716 13.250 1.0557 0.03580 0.03129 -0.0004 0.3516 0.8733 13.500 1.0579 0.03730 0.03274 0.0017 0.3358 0.8745 13.750 1.0571 0.03897 0.03435 0.0042 0.3184 0.8763 14.000 1.0584 0.04054 0.03586 0.0063 0.3009 0.8780 14.250 1.0578 0.04228 0.03755 0.0086 0.2838 0.8795 14.500 1.0607 0.04382 0.03904 0.0104 0.2676 0.8811 14.750 1.0606 0.04563 0.04078 0.0124 0.2502 0.8826 15.000 1.0642 0.04721 0.04231 0.0139 0.2350 0.8841 15.250 1.0665 0.04894 0.04397 0.0155 0.2186 0.8856 15.500 1.0694 0.05066 0.04563 0.0169 0.2043 0.8870 15.750 1.0742 0.05227 0.04719 0.0180 0.1906 0.8883 16.000 1.0766 0.05410 0.04896 0.0193 0.1764 0.8895 16.250 1.0818 0.05575 0.05056 0.0202 0.1644 0.8905 16.500 1.0894 0.05718 0.05198 0.0210 0.1544 0.8920 16.750 1.0926 0.05900 0.05376 0.0220 0.1435 0.8934 17.000 1.0959 0.06080 0.05552 0.0230 0.1320 0.8947 17.250 1.1039 0.06228 0.05700 0.0236 0.1247 0.8960 17.500 1.1084 0.06409 0.05880 0.0243 0.1172 0.8973 17.750 1.1145 0.06576 0.06046 0.0249 0.1099 0.8987 18.000 1.1218 0.06737 0.06207 0.0253 0.1041 0.9000 18.250 1.1276 0.06917 0.06388 0.0257 0.0988 0.9013 18.500 1.1328 0.07102 0.06572 0.0261 0.0928 0.9025 18.750 1.1415 0.07258 0.06731 0.0262 0.0885 0.9036 19.000 1.1451 0.07468 0.06939 0.0265 0.0835 0.9046 19.250 1.1532 0.07636 0.07111 0.0265 0.0807 0.9054