XFOIL Version 6.96 Calculated polar for: GEMINI (smoothed) 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -13.000 -0.5948 0.08648 0.08093 -0.0588 1.0000 0.0363 -12.750 -0.6286 0.07693 0.07125 -0.0653 1.0000 0.0360 -12.500 -0.6589 0.06951 0.06369 -0.0700 1.0000 0.0359 -12.250 -0.6862 0.06372 0.05772 -0.0726 1.0000 0.0358 -12.000 -0.7112 0.05913 0.05294 -0.0734 1.0000 0.0358 -11.750 -0.7344 0.05548 0.04908 -0.0724 1.0000 0.0358 -11.500 -0.7563 0.05257 0.04597 -0.0696 1.0000 0.0360 -11.250 -0.7776 0.05029 0.04349 -0.0652 1.0000 0.0361 -11.000 -0.7962 0.04819 0.04115 -0.0602 1.0000 0.0363 -10.750 -0.8053 0.04611 0.03892 -0.0563 1.0000 0.0367 -10.500 -0.8065 0.04455 0.03732 -0.0530 1.0000 0.0373 -10.250 -0.8072 0.04329 0.03601 -0.0496 1.0000 0.0380 -10.000 -0.8085 0.04209 0.03472 -0.0460 1.0000 0.0388 -9.750 -0.8100 0.04086 0.03336 -0.0421 1.0000 0.0398 -9.500 -0.8108 0.03956 0.03189 -0.0383 1.0000 0.0407 -9.250 -0.8048 0.03795 0.03003 -0.0358 0.9988 0.0419 -9.000 -0.7783 0.03567 0.02732 -0.0370 0.9929 0.0434 -8.750 -0.7497 0.03372 0.02512 -0.0384 0.9871 0.0451 -8.500 -0.7202 0.03239 0.02376 -0.0399 0.9812 0.0473 -8.250 -0.6897 0.03104 0.02225 -0.0413 0.9754 0.0497 -8.000 -0.6582 0.02963 0.02060 -0.0427 0.9697 0.0520 -7.750 -0.6292 0.02833 0.01917 -0.0436 0.9627 0.0545 -7.500 -0.5974 0.02720 0.01806 -0.0453 0.9572 0.0579 -7.250 -0.5693 0.02622 0.01698 -0.0459 0.9494 0.0613 -7.000 -0.5357 0.02517 0.01579 -0.0475 0.9443 0.0650 -6.750 -0.5094 0.02420 0.01485 -0.0479 0.9363 0.0696 -6.500 -0.4769 0.02334 0.01388 -0.0492 0.9305 0.0756 -6.250 -0.4528 0.02246 0.01301 -0.0490 0.9215 0.0814 -6.000 -0.4223 0.02166 0.01214 -0.0500 0.9151 0.0913 -5.750 -0.3991 0.02093 0.01142 -0.0494 0.9053 0.1035 -5.500 -0.3703 0.02002 0.01068 -0.0501 0.8989 0.1269 -5.250 -0.3495 0.01929 0.01017 -0.0491 0.8885 0.1702 -5.000 -0.3211 0.01854 0.00964 -0.0496 0.8821 0.2300 -4.750 -0.3000 0.01804 0.00929 -0.0486 0.8717 0.2769 -4.500 -0.2742 0.01749 0.00891 -0.0483 0.8641 0.3283 -4.250 -0.2515 0.01705 0.00865 -0.0474 0.8547 0.3797 -4.000 -0.2275 0.01668 0.00843 -0.0466 0.8463 0.4334 -3.750 -0.2038 0.01635 0.00828 -0.0456 0.8376 0.4903 -3.500 -0.1816 0.01614 0.00821 -0.0442 0.8286 0.5468 -3.250 -0.1558 0.01595 0.00810 -0.0433 0.8206 0.5920 -3.000 -0.1313 0.01585 0.00801 -0.0423 0.8113 0.6214 -2.750 -0.1022 0.01571 0.00781 -0.0422 0.8036 0.6469 -2.500 -0.0772 0.01565 0.00773 -0.0414 0.7939 0.6699 -2.250 -0.0475 0.01554 0.00755 -0.0414 0.7866 0.6934 -2.000 -0.0220 0.01552 0.00751 -0.0406 0.7765 0.7139 -1.750 0.0086 0.01545 0.00738 -0.0408 0.7690 0.7350 -1.500 0.0352 0.01544 0.00736 -0.0403 0.7591 0.7555 -1.250 0.0651 0.01543 0.00728 -0.0403 0.7509 0.7762 -1.000 0.0956 0.01544 0.00728 -0.0405 0.7417 0.7965 -0.750 0.1267 0.01549 0.00729 -0.0408 0.7328 0.8182 -0.500 0.1581 0.01553 0.00728 -0.0411 0.7241 0.8410 -0.250 0.1920 0.01563 0.00735 -0.0420 0.7144 0.8597 0.000 0.2278 0.01567 0.00730 -0.0433 0.7063 0.8754 0.250 0.2601 0.01576 0.00736 -0.0441 0.6957 0.8905 0.500 0.2981 0.01583 0.00735 -0.0460 0.6866 0.9025 0.750 0.3352 0.01591 0.00737 -0.0479 0.6767 0.9140 1.000 0.3706 0.01600 0.00740 -0.0494 0.6665 0.9260 1.250 0.4068 0.01605 0.00736 -0.0511 0.6577 0.9377 1.500 0.4475 0.01615 0.00743 -0.0539 0.6463 0.9458 1.750 0.4854 0.01624 0.00748 -0.0561 0.6360 0.9550 2.000 0.5232 0.01630 0.00747 -0.0583 0.6265 0.9644 2.250 0.5630 0.01640 0.00757 -0.0611 0.6148 0.9721 2.500 0.6012 0.01649 0.00762 -0.0635 0.6043 0.9809 2.750 0.6393 0.01656 0.00764 -0.0659 0.5944 0.9899 3.000 0.6777 0.01668 0.00778 -0.0686 0.5827 0.9986 3.250 0.7008 0.01679 0.00786 -0.0681 0.5727 1.0000 3.500 0.7201 0.01689 0.00792 -0.0667 0.5636 1.0000 3.750 0.7381 0.01705 0.00810 -0.0651 0.5534 1.0000 4.000 0.7575 0.01719 0.00821 -0.0636 0.5445 1.0000 4.250 0.7760 0.01737 0.00840 -0.0621 0.5347 1.0000 4.500 0.7949 0.01757 0.00859 -0.0605 0.5253 1.0000 4.750 0.8147 0.01776 0.00876 -0.0591 0.5164 1.0000 5.000 0.8331 0.01800 0.00905 -0.0575 0.5067 1.0000 5.250 0.8534 0.01823 0.00924 -0.0562 0.4983 1.0000 5.500 0.8718 0.01850 0.00956 -0.0546 0.4886 1.0000 5.750 0.8915 0.01877 0.00985 -0.0531 0.4798 1.0000 6.000 0.9108 0.01905 0.01015 -0.0516 0.4708 1.0000 6.250 0.9298 0.01936 0.01051 -0.0501 0.4618 1.0000 6.500 0.9499 0.01965 0.01082 -0.0488 0.4534 1.0000 6.750 0.9680 0.02001 0.01126 -0.0471 0.4442 1.0000 7.000 0.9885 0.02032 0.01157 -0.0458 0.4362 1.0000 7.250 1.0049 0.02068 0.01204 -0.0439 0.4256 1.0000 7.500 1.0207 0.02101 0.01242 -0.0418 0.4133 1.0000 7.750 1.0350 0.02134 0.01275 -0.0394 0.3993 1.0000 8.000 1.0477 0.02168 0.01311 -0.0367 0.3843 1.0000 8.250 1.0601 0.02207 0.01352 -0.0341 0.3697 1.0000 8.500 1.0722 0.02249 0.01397 -0.0315 0.3558 1.0000 8.750 1.0828 0.02295 0.01447 -0.0287 0.3411 1.0000 9.000 1.0912 0.02346 0.01502 -0.0256 0.3245 1.0000 9.250 1.0974 0.02403 0.01562 -0.0222 0.3077 1.0000 9.500 1.1014 0.02468 0.01628 -0.0185 0.2892 1.0000 9.750 1.1025 0.02553 0.01707 -0.0147 0.2670 1.0000 10.000 1.1033 0.02658 0.01807 -0.0113 0.2402 1.0000