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 = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.500 -0.8156 0.05053 0.04688 -0.0290 0.8075 0.0136 -10.250 -0.8364 0.04614 0.04216 -0.0260 0.8055 0.0136 -10.000 -0.8492 0.04130 0.03693 -0.0234 0.8037 0.0137 -9.750 -0.8418 0.03906 0.03455 -0.0223 0.8021 0.0140 -9.500 -0.7666 0.05015 0.04650 -0.0265 0.8002 0.0161 -9.250 -0.7862 0.04243 0.03827 -0.0235 0.7982 0.0153 -9.000 -0.7910 0.03622 0.03148 -0.0207 0.7964 0.0154 -8.750 -0.7821 0.03239 0.02716 -0.0189 0.7948 0.0162 -8.500 -0.7673 0.02965 0.02393 -0.0173 0.7933 0.0168 -8.250 -0.7513 0.02668 0.02051 -0.0161 0.7919 0.0174 -8.000 -0.7291 0.02551 0.01930 -0.0160 0.7906 0.0182 -7.750 -0.7051 0.02485 0.01859 -0.0158 0.7892 0.0189 -7.500 -0.6813 0.02327 0.01680 -0.0154 0.7880 0.0194 -7.250 -0.6564 0.02179 0.01514 -0.0151 0.7867 0.0199 -7.000 -0.6308 0.02058 0.01377 -0.0148 0.7851 0.0204 -6.750 -0.6049 0.01963 0.01268 -0.0146 0.7835 0.0210 -6.500 -0.5785 0.01901 0.01194 -0.0144 0.7820 0.0215 -6.250 -0.5549 0.01744 0.01036 -0.0140 0.7807 0.0226 -6.000 -0.5293 0.01690 0.00982 -0.0139 0.7794 0.0238 -5.750 -0.5037 0.01634 0.00922 -0.0137 0.7781 0.0250 -5.500 -0.4781 0.01580 0.00862 -0.0134 0.7769 0.0262 -5.250 -0.4542 0.01504 0.00781 -0.0129 0.7757 0.0275 -5.000 -0.4297 0.01450 0.00727 -0.0126 0.7744 0.0295 -4.750 -0.4036 0.01416 0.00691 -0.0125 0.7730 0.0318 -4.500 -0.3778 0.01368 0.00641 -0.0124 0.7718 0.0347 -4.250 -0.3511 0.01333 0.00609 -0.0124 0.7705 0.0386 -4.000 -0.3245 0.01296 0.00572 -0.0124 0.7691 0.0433 -3.750 -0.2974 0.01269 0.00546 -0.0125 0.7676 0.0505 -3.500 -0.2715 0.01222 0.00511 -0.0125 0.7660 0.0719 -3.250 -0.2480 0.01142 0.00477 -0.0123 0.7645 0.1687 -3.000 -0.2293 0.00996 0.00430 -0.0118 0.7631 0.4096 -2.750 -0.2124 0.00918 0.00478 -0.0098 0.7618 0.7112 -2.500 -0.1829 0.00954 0.00498 -0.0100 0.7605 0.7417 -2.250 -0.1546 0.00986 0.00526 -0.0098 0.7592 0.7544 -2.000 -0.1269 0.01016 0.00555 -0.0095 0.7580 0.7644 -1.750 -0.0989 0.01040 0.00581 -0.0093 0.7567 0.7756 -1.500 -0.0727 0.01075 0.00623 -0.0083 0.7550 0.7906 -1.250 -0.0475 0.01108 0.00661 -0.0071 0.7532 0.8052 -1.000 -0.0227 0.01138 0.00695 -0.0057 0.7514 0.8188 -0.750 0.0036 0.01147 0.00706 -0.0051 0.7496 0.8244 -0.500 0.0325 0.01146 0.00701 -0.0054 0.7478 0.8271 -0.250 0.0617 0.01145 0.00696 -0.0058 0.7462 0.8296 0.000 0.0914 0.01147 0.00692 -0.0064 0.7445 0.8316 0.250 0.1196 0.01142 0.00683 -0.0066 0.7427 0.8328 0.500 0.1487 0.01130 0.00674 -0.0072 0.7396 0.8337 0.750 0.1778 0.01121 0.00665 -0.0076 0.7363 0.8346 1.000 0.2068 0.01110 0.00653 -0.0079 0.7332 0.8354 1.250 0.2360 0.01099 0.00639 -0.0083 0.7307 0.8359 1.500 0.2651 0.01090 0.00626 -0.0086 0.7282 0.8364 1.750 0.2944 0.01081 0.00620 -0.0091 0.7238 0.8371 2.000 0.3237 0.01065 0.00604 -0.0094 0.7189 0.8377 2.250 0.3531 0.01043 0.00580 -0.0097 0.7147 0.8380 2.500 0.3824 0.01024 0.00560 -0.0100 0.7089 0.8383 2.750 0.4118 0.00999 0.00535 -0.0103 0.7017 0.8386 3.000 0.4411 0.00979 0.00511 -0.0105 0.6966 0.8391 3.250 0.4704 0.00961 0.00500 -0.0110 0.6885 0.8396 3.500 0.4998 0.00937 0.00473 -0.0112 0.6797 0.8399 3.750 0.5292 0.00920 0.00461 -0.0117 0.6698 0.8401 4.000 0.5587 0.00907 0.00452 -0.0121 0.6589 0.8403 4.250 0.5879 0.00891 0.00437 -0.0124 0.6406 0.8404 4.500 0.6164 0.00882 0.00421 -0.0126 0.6077 0.8406 4.750 0.6415 0.00911 0.00417 -0.0124 0.5275 0.8410 5.000 0.6627 0.01003 0.00458 -0.0120 0.4239 0.8415 5.250 0.6842 0.01093 0.00507 -0.0118 0.3345 0.8418 5.500 0.7057 0.01178 0.00554 -0.0116 0.2560 0.8420 5.750 0.7275 0.01257 0.00600 -0.0114 0.1913 0.8421 6.000 0.7496 0.01328 0.00644 -0.0113 0.1410 0.8423 6.250 0.7722 0.01392 0.00689 -0.0111 0.1060 0.8424 6.500 0.7950 0.01451 0.00734 -0.0109 0.0827 0.8425 6.750 0.8175 0.01510 0.00784 -0.0107 0.0680 0.8428 7.000 0.8412 0.01555 0.00828 -0.0105 0.0604 0.8432 7.250 0.8634 0.01613 0.00886 -0.0102 0.0545 0.8435 7.500 0.8864 0.01660 0.00934 -0.0099 0.0505 0.8436 7.750 0.9046 0.01747 0.01020 -0.0092 0.0462 0.8437 8.000 0.9272 0.01791 0.01070 -0.0089 0.0447 0.8438 8.250 0.9483 0.01846 0.01130 -0.0084 0.0430 0.8439 8.500 0.9681 0.01906 0.01193 -0.0078 0.0414 0.8440 8.750 0.9846 0.01972 0.01263 -0.0068 0.0400 0.8442 9.000 0.9992 0.02074 0.01366 -0.0058 0.0384 0.8446 9.250 1.0131 0.02194 0.01494 -0.0047 0.0371 0.8450 9.500 1.0329 0.02259 0.01564 -0.0043 0.0364 0.8452 9.750 1.0513 0.02337 0.01649 -0.0037 0.0355 0.8454 10.000 1.0691 0.02421 0.01740 -0.0031 0.0347 0.8455 10.250 1.0865 0.02508 0.01832 -0.0024 0.0338 0.8457 10.500 1.1036 0.02597 0.01928 -0.0017 0.0331 0.8459 10.750 1.1201 0.02691 0.02026 -0.0010 0.0323 0.8461 11.000 1.1359 0.02792 0.02130 -0.0003 0.0316 0.8463 11.250 1.1506 0.02929 0.02271 0.0008 0.0306 0.8465 11.500 1.1667 0.03093 0.02446 0.0019 0.0298 0.8467 11.750 1.1820 0.03195 0.02560 0.0026 0.0295 0.8470 12.000 1.1968 0.03309 0.02686 0.0034 0.0291 0.8473 12.250 1.2105 0.03434 0.02824 0.0042 0.0286 0.8477 12.500 1.2233 0.03570 0.02973 0.0051 0.0281 0.8481 12.750 1.2348 0.03717 0.03132 0.0060 0.0276 0.8485 13.000 1.2450 0.03869 0.03297 0.0068 0.0271 0.8490 13.250 1.2536 0.04025 0.03466 0.0077 0.0266 0.8495 13.500 1.2610 0.04185 0.03637 0.0085 0.0262 0.8500 13.750 1.2677 0.04352 0.03813 0.0092 0.0257 0.8506 14.000 1.2734 0.04534 0.04005 0.0099 0.0254 0.8512 14.250 1.2777 0.04740 0.04222 0.0107 0.0250 0.8519 14.500 1.2795 0.04988 0.04482 0.0115 0.0247 0.8528 14.750 1.2751 0.05323 0.04834 0.0125 0.0243 0.8536 15.000 1.2597 0.05799 0.05337 0.0134 0.0241 0.8542 15.250 1.2415 0.06277 0.05840 0.0137 0.0239 0.8548 15.500 1.2308 0.06646 0.06227 0.0134 0.0238 0.8555 15.750 1.2178 0.07066 0.06667 0.0127 0.0237 0.8563 16.000 1.2013 0.07578 0.07199 0.0114 0.0237 0.8570 16.250 1.1834 0.08157 0.07798 0.0092 0.0236 0.8578 16.500 1.1617 0.08845 0.08507 0.0061 0.0236 0.8586 16.750 1.1356 0.09675 0.09357 0.0018 0.0236 0.8593 17.000 1.1010 0.10739 0.10443 -0.0042 0.0237 0.8598 17.250 1.0544 0.12167 0.11893 -0.0129 0.0239 0.8600 17.500 1.0228 0.13430 0.13174 -0.0212 0.0241 0.8604