XFOIL Version 6.96 Calculated polar for: NACA 5-H-20 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -17.000 -0.8477 0.05650 0.05265 -0.0843 0.6753 0.0206 -16.750 -0.8822 0.04997 0.04589 -0.0864 0.6718 0.0206 -16.500 -0.8995 0.04621 0.04196 -0.0861 0.6674 0.0206 -16.250 -0.9150 0.04300 0.03858 -0.0848 0.6636 0.0206 -16.000 -0.9239 0.04054 0.03597 -0.0832 0.6595 0.0207 -15.750 -0.9275 0.03861 0.03390 -0.0813 0.6551 0.0207 -15.500 -0.9306 0.03678 0.03193 -0.0792 0.6508 0.0208 -15.250 -0.9337 0.03499 0.02998 -0.0769 0.6469 0.0208 -15.000 -0.9316 0.03358 0.02845 -0.0747 0.6436 0.0209 -14.750 -0.9271 0.03235 0.02711 -0.0726 0.6401 0.0209 -14.500 -0.9236 0.03105 0.02567 -0.0702 0.6362 0.0209 -14.250 -0.9232 0.02943 0.02389 -0.0675 0.6326 0.0211 -14.000 -0.9174 0.02822 0.02256 -0.0651 0.6290 0.0212 -13.750 -0.9083 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0.0972 0.500 0.3840 0.00963 0.00310 -0.0260 0.5283 0.2285 0.750 0.3851 0.00926 0.00304 -0.0210 0.5268 0.3319 1.000 0.3625 0.00877 0.00300 -0.0110 0.5256 0.4772 1.250 0.3442 0.00806 0.00276 -0.0019 0.5241 0.6198 1.500 0.3317 0.00751 0.00287 0.0065 0.5229 0.8144 1.750 0.3584 0.00765 0.00302 0.0066 0.5218 0.8293 2.000 0.3861 0.00778 0.00315 0.0065 0.5205 0.8351 2.250 0.4147 0.00803 0.00341 0.0062 0.5188 0.8426 2.500 0.4423 0.00827 0.00366 0.0061 0.5167 0.8488 2.750 0.4735 0.00859 0.00401 0.0054 0.5134 0.8529 3.000 0.5010 0.00877 0.00418 0.0052 0.5104 0.8554 3.250 0.5264 0.00887 0.00424 0.0053 0.5068 0.8563 3.500 0.5532 0.00888 0.00426 0.0051 0.5043 0.8566 3.750 0.5793 0.00892 0.00428 0.0050 0.5009 0.8569 4.000 0.6049 0.00896 0.00431 0.0051 0.4979 0.8571 4.250 0.6292 0.00902 0.00436 0.0053 0.4942 0.8574 4.500 0.6524 0.00911 0.00443 0.0057 0.4904 0.8577 4.750 0.6764 0.00918 0.00449 0.0060 0.4853 0.8579 5.000 0.6970 0.00931 0.00460 0.0068 0.4788 0.8582 5.250 0.7149 0.00948 0.00475 0.0081 0.4718 0.8586 5.500 0.7163 0.00984 0.00508 0.0122 0.4605 0.8593 5.750 0.7056 0.01066 0.00583 0.0180 0.4420 0.8601 6.000 0.6508 0.01296 0.00786 0.0301 0.3838 0.8613 6.250 0.6095 0.01511 0.00983 0.0395 0.3437 0.8628 6.500 0.6037 0.01628 0.01094 0.0436 0.3294 0.8634 6.750 0.6127 0.01697 0.01162 0.0456 0.3241 0.8639 7.000 0.6166 0.01790 0.01252 0.0482 0.3167 0.8644 7.250 0.6261 0.01867 0.01329 0.0499 0.3116 0.8649 7.500 0.6385 0.01936 0.01398 0.0513 0.3076 0.8654 7.750 0.6485 0.02016 0.01478 0.0529 0.3027 0.8658 8.000 0.6588 0.02100 0.01561 0.0543 0.2991 0.8662 8.250 0.6687 0.02187 0.01648 0.0558 0.2948 0.8666 8.500 0.6832 0.02255 0.01718 0.0567 0.2930 0.8669 8.750 0.6978 0.02322 0.01787 0.0576 0.2891 0.8673 9.000 0.7099 0.02404 0.01868 0.0587 0.2842 0.8676 9.250 0.7144 0.02530 0.01991 0.0605 0.2753 0.8681 9.500 0.7168 0.02671 0.02126 0.0624 0.2593 0.8685 9.750 0.7188 0.02817 0.02264 0.0642 0.2422 0.8690 10.000 0.7175 0.02986 0.02424 0.0663 0.2242 0.8695 10.250 0.7164 0.03156 0.02583 0.0682 0.2042 0.8699 10.500 0.7229 0.03284 0.02707 0.0694 0.1937 0.8703 10.750 0.7200 0.03471 0.02879 0.0714 0.1648 0.8708 11.000 0.7184 0.03652 0.03042 0.0731 0.1338 0.8712 11.250 0.7225 0.03806 0.03188 0.0743 0.1203 0.8716 11.500 0.7357 0.03902 0.03284 0.0747 0.1165 0.8719 11.750 0.7508 0.03988 0.03371 0.0750 0.1143 0.8722 12.000 0.7666 0.04071 0.03455 0.0751 0.1132 0.8725 12.250 0.7802 0.04169 0.03553 0.0754 0.1103 0.8728 12.500 0.7947 0.04264 0.03649 0.0756 0.1098 0.8731 12.750 0.8071 0.04373 0.03758 0.0759 0.1072 0.8734 13.000 0.8217 0.04467 0.03853 0.0760 0.1058 0.8737 13.250 0.8359 0.04565 0.03953 0.0762 0.1037 0.8739 13.500 0.8517 0.04653 0.04043 0.0762 0.1030 0.8742 13.750 0.8675 0.04741 0.04134 0.0761 0.1018 0.8745 14.000 0.8816 0.04844 0.04240 0.0762 0.1004 0.8747 14.250 0.8950 0.04954 0.04352 0.0762 0.0980 0.8750 14.500 0.9078 0.05067 0.04464 0.0763 0.0947 0.8752 14.750 0.9204 0.05181 0.04579 0.0763 0.0916 0.8755 15.000 0.9356 0.05277 0.04677 0.0762 0.0879 0.8757 15.250 0.9451 0.05419 0.04813 0.0763 0.0753 0.8759 15.500 0.9434 0.05659 0.05037 0.0769 0.0556 0.8763 15.750 0.9516 0.05822 0.05199 0.0769 0.0510 0.8769 16.000 0.9623 0.05964 0.05344 0.0768 0.0482 0.8775 16.250 0.9709 0.06129 0.05510 0.0767 0.0459 0.8780 16.500 0.9791 0.06299 0.05682 0.0766 0.0437 0.8785 16.750 0.9901 0.06444 0.05831 0.0764 0.0424 0.8790 17.000 1.0005 0.06595 0.05985 0.0761 0.0407 0.8794 17.250 1.0084 0.06774 0.06166 0.0759 0.0394 0.8798 17.500 1.0160 0.06955 0.06350 0.0757 0.0379 0.8802 17.750 1.0254 0.07119 0.06518 0.0754 0.0371 0.8806 18.000 1.0348 0.07286 0.06689 0.0750 0.0359 0.8811 18.250 1.0419 0.07479 0.06886 0.0747 0.0350 0.8815 18.500 1.0490 0.07671 0.07081 0.0743 0.0338 0.8819 18.750 1.0566 0.07861 0.07275 0.0739 0.0330 0.8824 19.000 1.0615 0.08083 0.07501 0.0734 0.0322 0.8828 19.250 1.0692 0.08273 0.07696 0.0729 0.0314 0.8832