XFOIL Version 6.96 Calculated polar for: AH 79-K-135/20 B 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.2033 0.08363 0.08113 -0.0749 0.7716 0.0120 -10.750 -0.2061 0.07874 0.07626 -0.0768 0.7710 0.0120 -10.500 -0.2121 0.07308 0.07061 -0.0790 0.7703 0.0129 -7.500 -0.4132 0.02151 0.01643 -0.0778 0.7598 0.0107 -7.250 -0.3907 0.02035 0.01522 -0.0771 0.7588 0.0099 -7.000 -0.3722 0.01830 0.01291 -0.0757 0.7577 0.0096 -6.750 -0.3500 0.01713 0.01159 -0.0749 0.7565 0.0096 -6.500 -0.3259 0.01645 0.01081 -0.0744 0.7552 0.0098 -6.250 -0.3029 0.01526 0.00949 -0.0737 0.7540 0.0096 -6.000 -0.2797 0.01427 0.00840 -0.0729 0.7528 0.0095 -5.750 -0.2562 0.01349 0.00753 -0.0722 0.7516 0.0094 -5.500 -0.2326 0.01281 0.00678 -0.0715 0.7505 0.0094 -5.250 -0.2086 0.01224 0.00614 -0.0709 0.7494 0.0095 -5.000 -0.1841 0.01176 0.00560 -0.0704 0.7483 0.0096 -4.750 -0.1591 0.01137 0.00514 -0.0700 0.7471 0.0099 -4.500 -0.1337 0.01108 0.00480 -0.0696 0.7458 0.0101 -4.250 -0.1094 0.01057 0.00426 -0.0690 0.7445 0.0113 -4.000 -0.0834 0.01029 0.00396 -0.0687 0.7430 0.0125 -3.750 -0.0569 0.01006 0.00371 -0.0686 0.7414 0.0138 -3.500 -0.0317 0.00966 0.00339 -0.0682 0.7398 0.0303 -3.250 -0.0055 0.00938 0.00320 -0.0680 0.7382 0.0543 -3.000 0.0210 0.00912 0.00303 -0.0679 0.7367 0.0773 -2.750 0.0465 0.00876 0.00284 -0.0677 0.7353 0.1290 -2.500 0.0712 0.00832 0.00267 -0.0675 0.7339 0.2093 -2.250 0.0940 0.00778 0.00253 -0.0669 0.7321 0.3348 -2.000 0.1144 0.00705 0.00239 -0.0659 0.7304 0.5021 -1.750 0.1352 0.00644 0.00227 -0.0648 0.7284 0.6476 -1.500 0.1596 0.00617 0.00223 -0.0641 0.7262 0.7218 -1.250 0.1864 0.00604 0.00220 -0.0639 0.7241 0.7608 -1.000 0.2141 0.00597 0.00214 -0.0638 0.7220 0.7843 -0.750 0.2418 0.00593 0.00212 -0.0638 0.7201 0.8046 -0.500 0.2698 0.00596 0.00214 -0.0638 0.7180 0.8204 -0.250 0.2974 0.00597 0.00217 -0.0637 0.7158 0.8327 0.000 0.3250 0.00600 0.00221 -0.0636 0.7132 0.8442 0.250 0.3526 0.00602 0.00224 -0.0635 0.7104 0.8526 0.500 0.3801 0.00606 0.00227 -0.0633 0.7078 0.8625 0.750 0.4077 0.00609 0.00231 -0.0632 0.7053 0.8690 1.000 0.4356 0.00614 0.00234 -0.0632 0.7024 0.8746 1.250 0.4629 0.00613 0.00236 -0.0631 0.6988 0.8786 1.500 0.4905 0.00612 0.00236 -0.0631 0.6951 0.8822 1.750 0.5185 0.00611 0.00234 -0.0632 0.6916 0.8856 2.000 0.5465 0.00612 0.00234 -0.0633 0.6876 0.8892 2.250 0.5739 0.00609 0.00234 -0.0633 0.6823 0.8921 2.500 0.6013 0.00606 0.00230 -0.0632 0.6767 0.8945 2.750 0.6287 0.00605 0.00232 -0.0632 0.6697 0.8969 3.000 0.6560 0.00605 0.00230 -0.0632 0.6629 0.8994 3.250 0.6836 0.00607 0.00234 -0.0633 0.6551 0.9019 3.500 0.7108 0.00611 0.00235 -0.0633 0.6467 0.9043 3.750 0.7365 0.00613 0.00235 -0.0630 0.6314 0.9065 4.000 0.7614 0.00621 0.00239 -0.0625 0.6128 0.9087 4.250 0.7841 0.00639 0.00248 -0.0616 0.5863 0.9113 4.500 0.8054 0.00665 0.00262 -0.0605 0.5533 0.9141 4.750 0.8258 0.00699 0.00280 -0.0592 0.5190 0.9170 5.000 0.8474 0.00726 0.00298 -0.0583 0.4911 0.9195 5.250 0.8678 0.00753 0.00316 -0.0570 0.4634 0.9222 5.500 0.8872 0.00785 0.00338 -0.0556 0.4338 0.9251 5.750 0.9047 0.00826 0.00365 -0.0539 0.3993 0.9284 6.000 0.9202 0.00875 0.00397 -0.0519 0.3585 0.9318 6.250 0.9340 0.00922 0.00427 -0.0495 0.3184 0.9356 6.500 0.9398 0.00994 0.00472 -0.0458 0.2606 0.9404 6.750 0.9421 0.01075 0.00524 -0.0415 0.2032 0.9458 7.000 0.9370 0.01149 0.00573 -0.0357 0.1519 0.9535 7.250 0.9293 0.01255 0.00649 -0.0300 0.0926 0.9636 7.500 0.9368 0.01396 0.00762 -0.0282 0.0335 0.9754 7.750 0.9632 0.01502 0.00857 -0.0299 0.0122 0.9845 8.000 0.9849 0.01569 0.00926 -0.0301 0.0108 1.0000 8.250 1.0018 0.01636 0.00998 -0.0294 0.0102 1.0000 8.500 1.0189 0.01704 0.01069 -0.0287 0.0098 1.0000 8.750 1.0351 0.01775 0.01145 -0.0278 0.0095 1.0000 9.000 1.0507 0.01850 0.01223 -0.0269 0.0092 1.0000 9.250 1.0657 0.01929 0.01306 -0.0259 0.0090 1.0000 9.500 1.0794 0.02016 0.01397 -0.0247 0.0086 1.0000 9.750 1.0923 0.02109 0.01495 -0.0236 0.0084 1.0000 10.000 1.1019 0.02225 0.01616 -0.0221 0.0080 1.0000 10.250 1.1112 0.02344 0.01743 -0.0206 0.0079 1.0000 10.500 1.1164 0.02493 0.01900 -0.0188 0.0077 1.0000 10.750 1.1197 0.02659 0.02074 -0.0169 0.0075 1.0000 11.000 1.1257 0.02809 0.02231 -0.0153 0.0075 1.0000 11.250 1.1370 0.02921 0.02348 -0.0143 0.0074 1.0000 11.500 1.1471 0.03043 0.02476 -0.0132 0.0072 1.0000 11.750 1.1540 0.03193 0.02632 -0.0119 0.0072 1.0000 12.000 1.1608 0.03344 0.02790 -0.0106 0.0071 1.0000 12.250 1.1667 0.03507 0.02961 -0.0094 0.0071 1.0000 12.500 1.1747 0.03658 0.03118 -0.0084 0.0069 1.0000 12.750 1.1775 0.03853 0.03321 -0.0069 0.0070 1.0000 13.000 1.1831 0.04032 0.03507 -0.0057 0.0070 1.0000 13.250 1.1914 0.04192 0.03674 -0.0050 0.0068 1.0000 13.500 1.1962 0.04385 0.03875 -0.0038 0.0069 1.0000 13.750 1.2016 0.04576 0.04075 -0.0026 0.0069 1.0000 14.000 1.2085 0.04760 0.04267 -0.0020 0.0067 1.0000 14.250 1.2143 0.04959 0.04475 -0.0012 0.0066 1.0000 14.500 1.2192 0.05169 0.04695 -0.0004 0.0065 1.0000 14.750 1.2231 0.05395 0.04933 0.0006 0.0066 1.0000 15.000 1.2263 0.05635 0.05184 0.0011 0.0065 1.0000 15.250 1.2276 0.05906 0.05468 0.0017 0.0064 1.0000 15.500 1.2286 0.06180 0.05753 0.0018 0.0062 1.0000 15.750 1.2257 0.06517 0.06107 0.0023 0.0063 1.0000 16.000 1.2250 0.06827 0.06426 0.0020 0.0061 1.0000 16.250 1.2204 0.07203 0.06817 0.0017 0.0062 1.0000 16.500 1.2175 0.07556 0.07179 0.0011 0.0060 1.0000 16.750 1.2081 0.08022 0.07663 0.0003 0.0060 1.0000 17.000 1.2126 0.08281 0.07920 -0.0009 0.0058 1.0000 17.250 1.1864 0.09049 0.08723 -0.0025 0.0060 1.0000 17.500 1.1481 0.10068 0.09781 -0.0055 0.0064 1.0000 17.750 1.1765 0.09923 0.09612 -0.0061 0.0058 1.0000 18.000 1.1118 0.11521 0.11268 -0.0123 0.0066 1.0000 18.250 1.0894 0.12378 0.12142 -0.0167 0.0069 1.0000