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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.9330 0.12446 0.11985 -0.0152 1.0000 0.0252 -16.750 -0.9729 0.11115 0.10630 -0.0232 1.0000 0.0250 -16.500 -1.0002 0.10138 0.09630 -0.0290 1.0000 0.0250 -16.250 -1.0215 0.09330 0.08800 -0.0338 1.0000 0.0251 -16.000 -1.0387 0.08638 0.08088 -0.0378 1.0000 0.0252 -15.750 -1.0527 0.08034 0.07462 -0.0411 1.0000 0.0253 -15.500 -1.0642 0.07496 0.06903 -0.0439 1.0000 0.0255 -15.250 -1.0725 0.07034 0.06422 -0.0461 1.0000 0.0256 -15.000 -1.0738 0.06699 0.06078 -0.0472 1.0000 0.0258 -14.750 -1.0743 0.06388 0.05759 -0.0482 1.0000 0.0261 -14.500 -1.0742 0.06089 0.05452 -0.0491 1.0000 0.0263 -14.250 -1.0733 0.05804 0.05158 -0.0499 1.0000 0.0266 -14.000 -1.0719 0.05531 0.04875 -0.0506 1.0000 0.0269 -13.750 -1.0696 0.05271 0.04605 -0.0511 1.0000 0.0272 -13.500 -1.0664 0.05027 0.04351 -0.0516 1.0000 0.0276 -13.250 -1.0623 0.04794 0.04107 -0.0519 1.0000 0.0280 -13.000 -1.0576 0.04574 0.03876 -0.0521 1.0000 0.0285 -12.750 -1.0520 0.04366 0.03656 -0.0522 1.0000 0.0290 -12.500 -1.0457 0.04171 0.03446 -0.0521 1.0000 0.0296 -12.250 -1.0387 0.03988 0.03250 -0.0520 1.0000 0.0302 -12.000 -1.0325 0.03810 0.03073 -0.0515 1.0000 0.0307 -11.750 -1.0262 0.03643 0.02903 -0.0510 1.0000 0.0313 -11.500 -1.0205 0.03484 0.02740 -0.0503 1.0000 0.0319 -11.250 -1.0166 0.03336 0.02587 -0.0491 1.0000 0.0324 -11.000 -1.0145 0.03195 0.02440 -0.0475 1.0000 0.0330 -10.750 -1.0076 0.03053 0.02292 -0.0466 1.0000 0.0338 -10.500 -0.9980 0.02915 0.02146 -0.0461 1.0000 0.0346 -10.250 -0.9863 0.02781 0.02004 -0.0458 1.0000 0.0355 -10.000 -0.9735 0.02640 0.01861 -0.0459 1.0000 0.0366 -9.750 -0.9578 0.02529 0.01745 -0.0457 1.0000 0.0381 -9.500 -0.9404 0.02430 0.01638 -0.0455 1.0000 0.0399 -9.250 -0.9217 0.02332 0.01533 -0.0453 1.0000 0.0417 -9.000 -0.9021 0.02228 0.01428 -0.0455 1.0000 0.0439 -8.750 -0.8809 0.02143 0.01336 -0.0455 1.0000 0.0466 -8.500 -0.8587 0.02057 0.01247 -0.0458 1.0000 0.0498 -8.250 -0.8356 0.01980 0.01169 -0.0460 1.0000 0.0545 -8.000 -0.8117 0.01903 0.01092 -0.0464 1.0000 0.0607 -7.750 -0.7871 0.01832 0.01023 -0.0468 1.0000 0.0690 -7.500 -0.7618 0.01767 0.00962 -0.0473 1.0000 0.0803 -7.250 -0.7361 0.01708 0.00906 -0.0477 1.0000 0.0945 -7.000 -0.7099 0.01655 0.00857 -0.0482 1.0000 0.1100 -6.750 -0.6832 0.01602 0.00810 -0.0488 1.0000 0.1263 -6.500 -0.6561 0.01551 0.00764 -0.0495 1.0000 0.1439 -6.250 -0.6285 0.01503 0.00722 -0.0501 1.0000 0.1628 -6.000 -0.6005 0.01455 0.00681 -0.0509 1.0000 0.1850 -5.750 -0.5711 0.01396 0.00637 -0.0521 1.0000 0.2189 -5.500 -0.5398 0.01324 0.00595 -0.0539 1.0000 0.2780 -5.250 -0.5089 0.01270 0.00575 -0.0554 1.0000 0.3482 -5.000 -0.4790 0.01252 0.00571 -0.0562 0.9996 0.3935 -4.750 -0.4468 0.01245 0.00569 -0.0573 0.9983 0.4207 -4.500 -0.4142 0.01243 0.00566 -0.0584 0.9968 0.4404 -4.250 -0.3814 0.01243 0.00565 -0.0595 0.9953 0.4544 -4.000 -0.3483 0.01246 0.00567 -0.0607 0.9940 0.4664 -3.750 -0.3173 0.01246 0.00565 -0.0614 0.9922 0.4769 -3.500 -0.2860 0.01249 0.00565 -0.0622 0.9904 0.4862 -3.250 -0.2546 0.01253 0.00570 -0.0630 0.9887 0.4951 -3.000 -0.2223 0.01258 0.00571 -0.0640 0.9871 0.5063 -2.750 -0.1902 0.01269 0.00588 -0.0648 0.9855 0.5167 -2.500 -0.1570 0.01280 0.00601 -0.0659 0.9841 0.5271 -2.250 -0.1272 0.01287 0.00610 -0.0663 0.9818 0.5349 -2.000 -0.0969 0.01290 0.00611 -0.0669 0.9796 0.5409 -1.750 -0.0662 0.01293 0.00621 -0.0675 0.9775 0.5447 -1.500 -0.0342 0.01296 0.00628 -0.0684 0.9755 0.5492 -1.250 -0.0012 0.01299 0.00632 -0.0695 0.9739 0.5541 -1.000 0.0319 0.01302 0.00639 -0.0707 0.9725 0.5584 -0.750 0.0636 0.01307 0.00652 -0.0715 0.9707 0.5620 -0.500 0.0937 0.01306 0.00659 -0.0719 0.9655 0.5660 -0.250 0.1723 0.01199 0.00557 -0.0808 0.9420 0.5717 0.000 0.2120 0.01139 0.00502 -0.0820 0.9130 0.5758 0.250 0.2470 0.01105 0.00473 -0.0824 0.8786 0.5793 0.500 0.2714 0.01186 0.00413 -0.0797 0.5282 0.5828 0.750 0.2833 0.01398 0.00464 -0.0773 0.1566 0.5864 1.000 0.3091 0.01454 0.00486 -0.0771 0.0898 0.5908 1.250 0.3356 0.01490 0.00513 -0.0767 0.0709 0.5942 1.500 0.3625 0.01521 0.00543 -0.0764 0.0622 0.5975 1.750 0.3896 0.01552 0.00576 -0.0761 0.0574 0.6012 2.000 0.4166 0.01586 0.00609 -0.0759 0.0536 0.6054 2.250 0.4436 0.01626 0.00647 -0.0757 0.0505 0.6097 2.500 0.4700 0.01662 0.00688 -0.0752 0.0477 0.6130 2.750 0.4962 0.01706 0.00733 -0.0748 0.0457 0.6166 3.000 0.5220 0.01765 0.00789 -0.0744 0.0442 0.6205 3.250 0.5490 0.01812 0.00841 -0.0741 0.0423 0.6250 3.500 0.5755 0.01860 0.00893 -0.0737 0.0404 0.6288 3.750 0.6016 0.01915 0.00949 -0.0733 0.0390 0.6325 4.000 0.6275 0.01994 0.01026 -0.0729 0.0379 0.6365 4.250 0.6546 0.02061 0.01104 -0.0726 0.0368 0.6408 4.500 0.6815 0.02128 0.01181 -0.0722 0.0352 0.6452 4.750 0.7078 0.02190 0.01251 -0.0718 0.0339 0.6490 5.000 0.7340 0.02264 0.01329 -0.0715 0.0330 0.6534 5.250 0.7603 0.02368 0.01439 -0.0712 0.0323 0.6581 5.500 0.7867 0.02486 0.01584 -0.0707 0.0314 0.6624 5.750 0.8121 0.02605 0.01730 -0.0700 0.0303 0.6665 6.000 0.8371 0.02704 0.01845 -0.0694 0.0293 0.6713 6.250 0.8619 0.02788 0.01938 -0.0690 0.0285 0.6767 6.500 0.8859 0.02886 0.02044 -0.0685 0.0279 0.6811 6.750 0.9078 0.03092 0.02293 -0.0673 0.0273 0.6854 7.000 0.9266 0.03386 0.02643 -0.0657 0.0266 0.6904 7.250 0.9425 0.03725 0.03035 -0.0638 0.0260 0.6957 7.500 0.9549 0.04087 0.03450 -0.0617 0.0254 0.6998 7.750 0.9671 0.04398 0.03799 -0.0598 0.0248 0.7046 8.000 0.9811 0.04614 0.04037 -0.0584 0.0243 0.7101 8.250 0.9969 0.04751 0.04186 -0.0572 0.0240 0.7154 8.500 1.0110 0.04894 0.04342 -0.0559 0.0237 0.7211 8.750 0.9994 0.05574 0.05081 -0.0525 0.0233 0.7255 9.000 0.9749 0.06450 0.06011 -0.0492 0.0232 0.7291 9.250 0.9513 0.07176 0.06772 -0.0471 0.0232 0.7323 9.500 0.9275 0.07713 0.07328 -0.0452 0.0233 0.7366 9.750 0.9033 0.08345 0.07975 -0.0459 0.0233 0.7411