XFOIL Version 6.96 Calculated polar for: HSNLF(1)-0213 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.4247 0.09828 0.09422 -0.0432 1.0000 0.1330 -10.250 -0.3795 0.09631 0.09220 -0.0377 1.0000 0.1427 -10.000 -0.4108 0.09194 0.08791 -0.0411 1.0000 0.1472 -9.750 -0.4473 0.08844 0.08450 -0.0421 1.0000 0.1478 -9.500 -0.5168 0.08801 0.08384 -0.0377 1.0000 0.1400 -9.250 -0.5365 0.08291 0.07876 -0.0426 1.0000 0.1443 -9.000 -0.5691 0.08068 0.07657 -0.0409 1.0000 0.1442 -8.750 -0.6036 0.07933 0.07523 -0.0368 0.9988 0.1435 -8.500 -0.6614 0.07714 0.07252 -0.0400 0.9861 0.1484 -8.250 -0.6148 0.07144 0.06718 -0.0399 0.9868 0.1582 -8.000 -0.6142 0.06762 0.06326 -0.0412 0.9828 0.1698 -6.750 -0.6028 0.04288 0.03512 -0.0341 0.9620 0.0747 -6.500 -0.5813 0.03866 0.03073 -0.0341 0.9597 0.0720 -6.250 -0.5569 0.03587 0.02754 -0.0338 0.9576 0.0708 -6.000 -0.5308 0.03394 0.02518 -0.0337 0.9559 0.0725 -5.750 -0.5080 0.03226 0.02313 -0.0328 0.9543 0.0734 -5.500 -0.4897 0.03089 0.02147 -0.0310 0.9521 0.0741 -5.250 -0.4658 0.02919 0.01961 -0.0302 0.9499 0.0764 -5.000 -0.4416 0.02795 0.01842 -0.0300 0.9479 0.0817 -4.750 -0.4162 0.02700 0.01736 -0.0295 0.9464 0.0861 -4.500 -0.3899 0.02585 0.01626 -0.0293 0.9447 0.0927 -4.250 -0.3625 0.02513 0.01554 -0.0294 0.9427 0.1031 -4.000 -0.3366 0.02416 0.01474 -0.0295 0.9409 0.1188 -3.750 -0.3205 0.02331 0.01410 -0.0278 0.9393 0.1467 -3.500 -0.3240 0.02054 0.01340 -0.0236 0.9374 0.4559 -3.250 -0.3357 0.02250 0.01639 -0.0114 0.9347 0.7775 -3.000 -0.0403 0.02717 0.02033 -0.0425 0.9442 0.9390 -2.750 0.0322 0.02650 0.01943 -0.0516 0.9443 0.9574 -2.500 0.0783 0.02612 0.01890 -0.0564 0.9429 0.9677 -2.250 0.1278 0.02561 0.01826 -0.0619 0.9413 0.9755 -2.000 0.1635 0.02544 0.01800 -0.0648 0.9392 0.9830 -1.750 0.1986 0.02521 0.01770 -0.0678 0.9366 0.9894 -1.500 0.2314 0.02511 0.01754 -0.0703 0.9337 0.9949 -1.250 0.2700 0.02493 0.01731 -0.0739 0.9310 0.9997 -1.000 0.2949 0.02506 0.01741 -0.0747 0.9277 1.0000 -0.750 0.3196 0.02525 0.01758 -0.0753 0.9245 1.0000 -0.500 0.3190 0.02589 0.01822 -0.0715 0.9188 1.0000 -0.250 0.3376 0.02621 0.01853 -0.0710 0.9143 1.0000 0.000 0.3686 0.02637 0.01869 -0.0726 0.9106 1.0000 0.250 0.3636 0.02714 0.01947 -0.0678 0.9038 1.0000 0.500 0.3855 0.02746 0.01981 -0.0678 0.8985 1.0000 0.750 0.4142 0.02775 0.02012 -0.0688 0.8936 1.0000 1.000 0.4134 0.02843 0.02083 -0.0647 0.8852 1.0000 1.250 0.4541 0.02853 0.02098 -0.0676 0.8803 1.0000 1.500 0.4489 0.02932 0.02180 -0.0627 0.8705 1.0000 1.750 0.4939 0.02935 0.02189 -0.0660 0.8650 1.0000 2.000 0.4915 0.03007 0.02266 -0.0615 0.8538 1.0000 2.250 0.5081 0.03051 0.02316 -0.0600 0.8439 1.0000 2.500 0.5500 0.03038 0.02313 -0.0621 0.8355 1.0000 2.750 0.5626 0.03073 0.02355 -0.0596 0.8226 1.0000 3.000 0.5826 0.03085 0.02375 -0.0580 0.8097 1.0000 3.250 0.6090 0.03062 0.02361 -0.0569 0.7959 1.0000 3.500 0.6364 0.03007 0.02318 -0.0553 0.7811 1.0000 3.750 0.6626 0.02932 0.02252 -0.0532 0.7662 1.0000 4.000 0.6872 0.02846 0.02176 -0.0507 0.7521 1.0000 4.250 0.7109 0.02742 0.02083 -0.0479 0.7381 1.0000 4.500 0.7332 0.02622 0.01973 -0.0447 0.7232 1.0000 4.750 0.7542 0.02490 0.01851 -0.0414 0.7071 1.0000 5.000 0.7745 0.02355 0.01730 -0.0380 0.6893 1.0000 5.250 0.7952 0.02205 0.01593 -0.0347 0.6700 1.0000 5.500 0.8127 0.02091 0.01494 -0.0316 0.6422 1.0000 5.750 0.8289 0.01986 0.01402 -0.0283 0.5944 1.0000 6.000 0.8447 0.01836 0.01159 -0.0225 0.4392 1.0000 6.250 0.8370 0.02040 0.01242 -0.0174 0.2803 1.0000 6.500 0.8317 0.02220 0.01352 -0.0129 0.2046 1.0000 6.750 0.8316 0.02350 0.01448 -0.0089 0.1704 1.0000 7.000 0.8331 0.02462 0.01535 -0.0051 0.1514 1.0000 7.250 0.8376 0.02555 0.01616 -0.0016 0.1371 1.0000 7.500 0.8445 0.02635 0.01696 0.0016 0.1261 1.0000 7.750 0.8577 0.02740 0.01795 0.0039 0.1178 1.0000 8.000 0.8723 0.02835 0.01884 0.0059 0.1108 1.0000 8.250 0.8932 0.02964 0.02013 0.0070 0.1044 1.0000 8.500 0.9068 0.03054 0.02112 0.0091 0.0992 1.0000 8.750 0.9391 0.03260 0.02303 0.0082 0.0941 1.0000 9.000 0.9577 0.03405 0.02473 0.0096 0.0918 1.0000 9.250 0.9777 0.03572 0.02669 0.0105 0.0893 1.0000 9.500 0.9980 0.03746 0.02863 0.0111 0.0863 1.0000 9.750 1.0192 0.03929 0.03059 0.0113 0.0834 1.0000 10.000 1.0417 0.04207 0.03351 0.0111 0.0816 1.0000 10.250 1.0605 0.04602 0.03773 0.0112 0.0807 1.0000 10.500 1.0722 0.04915 0.04125 0.0121 0.0804 1.0000 10.750 1.0795 0.05226 0.04477 0.0134 0.0801 1.0000 11.000 1.0817 0.05545 0.04837 0.0149 0.0797 1.0000 11.250 1.0790 0.05884 0.05217 0.0165 0.0794 1.0000 11.500 1.0725 0.06255 0.05621 0.0181 0.0794 1.0000 11.750 1.0645 0.06667 0.06057 0.0196 0.0798 1.0000 12.000 1.0673 0.07219 0.06625 0.0197 0.0807 1.0000 12.250 1.0117 0.07455 0.06911 0.0227 0.0826 1.0000 12.500 0.9107 0.08662 0.08167 0.0193 0.0883 1.0000 12.750 0.8764 0.09542 0.09058 0.0154 0.0911 1.0000 13.000 0.8677 0.10196 0.09715 0.0133 0.0927 1.0000