XFOIL Version 6.96 Calculated polar for: AH 88-K-136/16 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 ------ -------- --------- --------- -------- -------- -------- -15.250 -0.8205 0.04626 0.04310 -0.1020 0.7789 0.0049 -15.000 -0.8578 0.04021 0.03684 -0.1030 0.7780 0.0049 -14.750 -0.8732 0.03717 0.03366 -0.1015 0.7772 0.0050 -14.500 -0.8868 0.03457 0.03092 -0.0990 0.7762 0.0051 -14.250 -0.8969 0.03241 0.02860 -0.0960 0.7753 0.0051 -14.000 -0.9060 0.03041 0.02643 -0.0925 0.7744 0.0051 -13.750 -0.9087 0.02884 0.02471 -0.0892 0.7737 0.0052 -13.500 -0.9009 0.02791 0.02370 -0.0869 0.7730 0.0053 -13.250 -0.9027 0.02642 0.02204 -0.0832 0.7723 0.0053 -13.000 -0.8956 0.02546 0.02098 -0.0805 0.7716 0.0054 -12.750 -0.8891 0.02446 0.01986 -0.0776 0.7709 0.0055 -12.500 -0.8792 0.02365 0.01896 -0.0751 0.7702 0.0056 -12.250 -0.8701 0.02277 0.01798 -0.0723 0.7694 0.0057 -12.000 -0.8590 0.02203 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0.00248 -0.0263 0.6722 0.9402 2.500 0.4774 0.00614 0.00246 -0.0252 0.6658 0.9421 2.750 0.4999 0.00614 0.00244 -0.0242 0.6580 0.9433 3.000 0.5274 0.00616 0.00245 -0.0243 0.6492 0.9440 3.250 0.5546 0.00621 0.00247 -0.0244 0.6376 0.9447 3.500 0.5809 0.00629 0.00251 -0.0243 0.6234 0.9456 3.750 0.6059 0.00640 0.00258 -0.0240 0.6075 0.9464 4.000 0.6287 0.00658 0.00268 -0.0232 0.5848 0.9474 4.250 0.6498 0.00680 0.00281 -0.0221 0.5616 0.9486 4.500 0.6706 0.00701 0.00297 -0.0210 0.5411 0.9500 4.750 0.6882 0.00730 0.00316 -0.0192 0.5168 0.9519 5.000 0.7046 0.00755 0.00335 -0.0172 0.4943 0.9539 5.250 0.7193 0.00780 0.00353 -0.0149 0.4748 0.9560 5.500 0.7315 0.00807 0.00374 -0.0121 0.4558 0.9579 5.750 0.7491 0.00844 0.00403 -0.0106 0.4282 0.9595 6.000 0.7605 0.00910 0.00450 -0.0083 0.3854 0.9620 6.250 0.7650 0.00980 0.00503 -0.0047 0.3466 0.9653 6.500 0.7638 0.01055 0.00564 -0.0001 0.3117 0.9696 6.750 0.7713 0.01155 0.00645 0.0019 0.2688 0.9726 7.000 0.7895 0.01255 0.00721 0.0017 0.2205 0.9740 7.250 0.8076 0.01362 0.00802 0.0014 0.1694 0.9751 7.500 0.8255 0.01451 0.00871 0.0016 0.1315 0.9764 7.750 0.8399 0.01549 0.00948 0.0023 0.0905 0.9779 8.000 0.8541 0.01643 0.01025 0.0031 0.0569 0.9795 8.250 0.8701 0.01724 0.01095 0.0038 0.0359 0.9809 8.500 0.8872 0.01795 0.01159 0.0044 0.0235 0.9824 8.750 0.9071 0.01849 0.01213 0.0047 0.0198 0.9836 9.000 0.9284 0.01914 0.01277 0.0046 0.0164 0.9842 9.250 0.9503 0.01972 0.01337 0.0043 0.0146 0.9849 9.500 0.9706 0.02039 0.01404 0.0043 0.0127 0.9856 9.750 0.9920 0.02098 0.01466 0.0042 0.0117 0.9864 10.000 1.0121 0.02163 0.01533 0.0041 0.0107 0.9873 10.250 1.0303 0.02241 0.01612 0.0044 0.0097 0.9884 10.500 1.0494 0.02310 0.01685 0.0045 0.0091 0.9895 10.750 1.0678 0.02385 0.01764 0.0047 0.0087 0.9908 11.000 1.0859 0.02459 0.01841 0.0049 0.0081 0.9922 11.250 1.1018 0.02545 0.01930 0.0053 0.0075 0.9936 12.000 1.1478 0.02824 0.02221 0.0069 0.0065 1.0000 12.250 1.1565 0.02915 0.02315 0.0087 0.0062 1.0000 12.500 1.1665 0.03011 0.02416 0.0101 0.0060 1.0000 12.750 1.1775 0.03109 0.02518 0.0113 0.0058 1.0000 13.000 1.1879 0.03217 0.02630 0.0124 0.0055 1.0000 13.250 1.1978 0.03334 0.02751 0.0134 0.0053 1.0000 13.500 1.2063 0.03466 0.02889 0.0146 0.0052 1.0000 13.750 1.2127 0.03619 0.03047 0.0157 0.0049 1.0000 14.000 1.2218 0.03754 0.03189 0.0166 0.0048 1.0000 14.250 1.2305 0.03897 0.03338 0.0174 0.0046 1.0000 14.500 1.2363 0.04069 0.03518 0.0183 0.0047 1.0000 14.750 1.2466 0.04202 0.03658 0.0189 0.0045 1.0000 15.000 1.2526 0.04379 0.03841 0.0196 0.0043 1.0000 15.250 1.2589 0.04559 0.04028 0.0202 0.0043 1.0000 15.500 1.2608 0.04787 0.04266 0.0210 0.0043 1.0000 15.750 1.2680 0.04965 0.04450 0.0213 0.0041 1.0000 16.000 1.2711 0.05189 0.04682 0.0218 0.0040 1.0000 16.250 1.2756 0.05404 0.04904 0.0220 0.0039 1.0000 16.500 1.2780 0.05649 0.05157 0.0222 0.0038 1.0000 16.750 1.2844 0.05852 0.05366 0.0222 0.0036 1.0000 17.000 1.2808 0.06176 0.05702 0.0223 0.0037 1.0000 17.250 1.2812 0.06460 0.05993 0.0222 0.0036 1.0000 17.500 1.2849 0.06710 0.06249 0.0219 0.0035 1.0000 17.750 1.2795 0.07082 0.06632 0.0215 0.0035 1.0000 18.000 1.2738 0.07466 0.07026 0.0209 0.0033 1.0000 18.250 1.2656 0.07892 0.07464 0.0201 0.0032 1.0000 18.500 1.2631 0.08251 0.07833 0.0193 0.0034 1.0000 18.750 1.2521 0.08739 0.08333 0.0181 0.0033 1.0000 19.000 1.2448 0.09184 0.08788 0.0168 0.0032 1.0000 19.250 1.2407 0.09587 0.09201 0.0155 0.0032 1.0000