XFOIL Version 6.96 Calculated polar for: NPL 9510 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.750 -0.8005 0.11882 0.11459 -0.0225 1.0000 0.0483 -14.500 -0.8242 0.10857 0.10429 -0.0274 1.0000 0.0473 -14.250 -0.8842 0.09179 0.08735 -0.0381 1.0000 0.0459 -14.000 -0.9399 0.07888 0.07417 -0.0467 1.0000 0.0448 -13.750 -0.9851 0.06927 0.06425 -0.0527 1.0000 0.0440 -13.500 -1.0174 0.06227 0.05695 -0.0564 1.0000 0.0436 -13.250 -1.0384 0.05713 0.05154 -0.0585 1.0000 0.0435 -13.000 -1.0523 0.05303 0.04721 -0.0597 1.0000 0.0435 -12.750 -1.0616 0.04958 0.04355 -0.0601 1.0000 0.0436 -12.500 -1.0683 0.04666 0.04042 -0.0597 1.0000 0.0438 -12.250 -1.0721 0.04412 0.03770 -0.0590 1.0000 0.0441 -12.000 -1.0690 0.04169 0.03507 -0.0587 1.0000 0.0445 -11.750 -1.0626 0.03951 0.03269 -0.0579 1.0000 0.0450 -11.500 -1.0539 0.03751 0.03049 -0.0570 1.0000 0.0456 -11.250 -1.0431 0.03569 0.02848 -0.0560 1.0000 0.0464 -11.000 -1.0310 0.03411 0.02666 -0.0551 1.0000 0.0474 -10.750 -1.0172 0.03256 0.02489 -0.0542 1.0000 0.0484 -10.500 -1.0002 0.03079 0.02318 -0.0528 1.0000 0.0497 -10.250 -0.9836 0.02958 0.02197 -0.0517 1.0000 0.0510 -10.000 -0.9667 0.02842 0.02075 -0.0507 1.0000 0.0524 -9.750 -0.9494 0.02731 0.01954 -0.0496 1.0000 0.0541 -9.500 -0.9313 0.02631 0.01841 -0.0486 1.0000 0.0558 -9.250 -0.9152 0.02493 0.01714 -0.0475 1.0000 0.0582 -9.000 -0.8964 0.02399 0.01619 -0.0468 1.0000 0.0612 -8.750 -0.8762 0.02312 0.01521 -0.0463 1.0000 0.0646 -8.500 -0.8573 0.02183 0.01403 -0.0459 1.0000 0.0687 -8.250 -0.8352 0.02098 0.01313 -0.0458 1.0000 0.0743 -8.000 -0.8128 0.01989 0.01211 -0.0461 1.0000 0.0822 -7.750 -0.7887 0.01889 0.01117 -0.0467 1.0000 0.0941 -7.500 -0.7632 0.01787 0.01022 -0.0474 1.0000 0.1123 -7.250 -0.7367 0.01691 0.00939 -0.0485 1.0000 0.1362 -7.000 -0.7094 0.01608 0.00867 -0.0496 1.0000 0.1612 -6.750 -0.6815 0.01532 0.00801 -0.0506 1.0000 0.1882 -6.500 -0.6522 0.01445 0.00734 -0.0521 1.0000 0.2237 -6.250 -0.6213 0.01349 0.00672 -0.0541 1.0000 0.2847 -6.000 -0.5909 0.01285 0.00646 -0.0555 1.0000 0.3630 -5.750 -0.5631 0.01274 0.00647 -0.0558 1.0000 0.4125 -5.500 -0.5364 0.01282 0.00658 -0.0556 1.0000 0.4441 -5.250 -0.5105 0.01301 0.00679 -0.0552 1.0000 0.4676 -5.000 -0.4849 0.01324 0.00698 -0.0547 1.0000 0.4853 -4.750 -0.4596 0.01345 0.00719 -0.0540 1.0000 0.4982 -4.500 -0.4337 0.01363 0.00732 -0.0536 1.0000 0.5099 -4.250 -0.4080 0.01381 0.00746 -0.0531 1.0000 0.5200 -4.000 -0.3827 0.01395 0.00761 -0.0525 1.0000 0.5279 -3.750 -0.3568 0.01411 0.00773 -0.0521 1.0000 0.5368 -3.500 -0.3312 0.01422 0.00785 -0.0516 1.0000 0.5437 -3.250 -0.3061 0.01437 0.00801 -0.0510 1.0000 0.5506 -3.000 -0.2794 0.01447 0.00806 -0.0509 1.0000 0.5588 -2.750 -0.2559 0.01469 0.00836 -0.0499 1.0000 0.5651 -2.500 -0.2293 0.01486 0.00848 -0.0498 1.0000 0.5750 -2.250 -0.2075 0.01515 0.00890 -0.0482 1.0000 0.5816 -2.000 -0.1812 0.01533 0.00905 -0.0481 1.0000 0.5910 -1.750 -0.1570 0.01544 0.00923 -0.0473 1.0000 0.5957 -1.500 -0.1319 0.01554 0.00938 -0.0469 1.0000 0.6004 -1.250 -0.1047 0.01559 0.00942 -0.0471 1.0000 0.6061 -1.000 -0.0774 0.01561 0.00945 -0.0473 1.0000 0.6110 -0.750 -0.0527 0.01572 0.00964 -0.0468 1.0000 0.6147 -0.500 -0.0270 0.01583 0.00981 -0.0466 1.0000 0.6193 -0.250 0.0005 0.01592 0.00990 -0.0470 1.0000 0.6249 0.000 0.0267 0.01601 0.01006 -0.0470 1.0000 0.6290 0.250 0.0514 0.01616 0.01032 -0.0466 1.0000 0.6327 0.500 0.1939 0.01504 0.00939 -0.0678 0.9601 0.6399 0.750 0.2802 0.01330 0.00782 -0.0771 0.9232 0.6455 1.000 0.3041 0.01465 0.00665 -0.0728 0.2826 0.6487 1.250 0.3227 0.01616 0.00725 -0.0713 0.1037 0.6525 1.500 0.3493 0.01664 0.00764 -0.0710 0.0898 0.6572 1.750 0.3758 0.01723 0.00813 -0.0708 0.0824 0.6621 2.000 0.4014 0.01762 0.00857 -0.0700 0.0768 0.6656 2.250 0.4265 0.01835 0.00923 -0.0694 0.0724 0.6696 2.500 0.4537 0.01905 0.00994 -0.0691 0.0699 0.6742 2.750 0.4825 0.01965 0.01053 -0.0691 0.0670 0.6793 3.000 0.5088 0.02026 0.01116 -0.0686 0.0639 0.6829 3.250 0.5361 0.02137 0.01223 -0.0683 0.0619 0.6872 3.500 0.5653 0.02268 0.01361 -0.0683 0.0606 0.6921 3.750 0.5945 0.02345 0.01455 -0.0683 0.0589 0.6969 4.000 0.6215 0.02443 0.01574 -0.0676 0.0570 0.7007 4.250 0.6492 0.02588 0.01742 -0.0671 0.0564 0.7055 4.500 0.6774 0.02782 0.01963 -0.0667 0.0567 0.7109 4.750 0.7034 0.02994 0.02209 -0.0658 0.0569 0.7151 5.000 0.7275 0.03241 0.02496 -0.0646 0.0576 0.7191 5.250 0.7530 0.03570 0.02832 -0.0641 0.0620 0.7241 5.500 0.7235 0.03137 0.02576 -0.0512 0.0983 0.7195 5.750 0.7364 0.03412 0.02912 -0.0489 0.0882 0.7247 6.000 0.7547 0.03669 0.03165 -0.0484 0.0858 0.7301 6.250 0.7582 0.04160 0.03701 -0.0461 0.0803 0.7335 6.500 0.8327 0.05561 0.05072 -0.0543 0.0744 0.7469 6.750 0.8493 0.05838 0.05348 -0.0536 0.0731 0.7518 7.000 0.8611 0.06609 0.06100 -0.0541 0.0716 0.7571 7.250 0.8534 0.06718 0.06309 -0.0504 0.0658 0.7619 7.500 0.8603 0.07026 0.06632 -0.0493 0.0641 0.7665 7.750 0.8689 0.07319 0.06932 -0.0484 0.0630 0.7722 8.000 0.8802 0.07628 0.07239 -0.0477 0.0622 0.7785 8.250 0.8954 0.08059 0.07662 -0.0474 0.0615 0.7843 8.500 0.8839 0.08686 0.08309 -0.0466 0.0609 0.7894 8.750 0.8393 0.09185 0.08850 -0.0463 0.0602 0.7935 9.000 0.8038 0.09949 0.09631 -0.0522 0.0593 0.7973