XFOIL Version 6.96 Calculated polar for: Joukovsky f=0% t=9% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -10.250 -0.7680 0.08649 0.07946 0.0059 1.0000 0.0583 -10.000 -0.8509 0.06953 0.06217 -0.0099 1.0000 0.0545 -9.750 -0.8646 0.06462 0.05708 -0.0114 1.0000 0.0547 -9.500 -0.8667 0.06054 0.05284 -0.0121 1.0000 0.0555 -9.250 -0.8664 0.05647 0.04853 -0.0126 1.0000 0.0563 -9.000 -0.8622 0.05262 0.04439 -0.0128 1.0000 0.0574 -8.750 -0.8537 0.04922 0.04070 -0.0128 1.0000 0.0593 -8.500 -0.8434 0.04583 0.03688 -0.0127 1.0000 0.0624 -8.250 -0.8313 0.04220 0.03258 -0.0125 1.0000 0.0655 -8.000 -0.8131 0.03947 0.02969 -0.0121 1.0000 0.0683 -7.750 -0.7933 0.03728 0.02728 -0.0117 1.0000 0.0722 -7.500 -0.7727 0.03497 0.02446 -0.0112 1.0000 0.0782 -7.250 -0.7511 0.03312 0.02265 -0.0107 1.0000 0.0835 -7.000 -0.7281 0.03128 0.02047 -0.0101 1.0000 0.0911 -6.750 -0.7060 0.02976 0.01899 -0.0096 1.0000 0.0998 -6.500 -0.6830 0.02820 0.01731 -0.0090 1.0000 0.1098 -6.250 -0.6601 0.02685 0.01591 -0.0084 1.0000 0.1236 -6.000 -0.6371 0.02554 0.01461 -0.0079 1.0000 0.1401 -5.750 -0.6139 0.02432 0.01338 -0.0074 1.0000 0.1624 -5.500 -0.5908 0.02319 0.01230 -0.0069 1.0000 0.1905 -5.250 -0.5678 0.02213 0.01143 -0.0065 1.0000 0.2240 -5.000 -0.5443 0.02123 0.01065 -0.0060 1.0000 0.2647 -4.750 -0.5206 0.02046 0.01003 -0.0055 1.0000 0.3089 -4.500 -0.4968 0.01981 0.00949 -0.0049 1.0000 0.3542 -4.250 -0.4731 0.01926 0.00906 -0.0041 1.0000 0.3987 -4.000 -0.4495 0.01880 0.00871 -0.0031 1.0000 0.4415 -3.750 -0.4260 0.01840 0.00841 -0.0020 1.0000 0.4819 -3.500 -0.4023 0.01804 0.00811 -0.0009 1.0000 0.5211 -3.250 -0.3788 0.01772 0.00787 0.0004 1.0000 0.5579 -3.000 -0.3553 0.01742 0.00763 0.0016 1.0000 0.5943 -2.750 -0.3322 0.01715 0.00744 0.0031 1.0000 0.6279 -2.500 -0.3094 0.01690 0.00724 0.0046 1.0000 0.6609 -2.250 -0.2870 0.01666 0.00708 0.0062 1.0000 0.6934 -2.000 -0.2649 0.01644 0.00693 0.0079 1.0000 0.7255 -1.750 -0.2433 0.01623 0.00678 0.0096 1.0000 0.7578 -1.500 -0.2217 0.01603 0.00665 0.0113 1.0000 0.7906 -1.250 -0.1991 0.01584 0.00655 0.0128 1.0000 0.8238 -1.000 -0.1731 0.01569 0.00646 0.0136 1.0000 0.8584 -0.750 -0.1407 0.01556 0.00637 0.0129 1.0000 0.8950 -0.500 -0.0978 0.01546 0.00629 0.0099 1.0000 0.9307 -0.250 -0.0479 0.01536 0.00620 0.0051 1.0000 0.9655 0.000 0.0000 0.01528 0.00613 0.0000 1.0000 1.0000 0.250 0.0479 0.01537 0.00620 -0.0051 0.9654 1.0000 0.500 0.0979 0.01546 0.00629 -0.0099 0.9307 1.0000 0.750 0.1407 0.01556 0.00637 -0.0129 0.8950 1.0000 1.000 0.1731 0.01568 0.00646 -0.0136 0.8584 1.0000 1.250 0.1991 0.01584 0.00655 -0.0128 0.8238 1.0000 1.500 0.2217 0.01603 0.00665 -0.0113 0.7906 1.0000 1.750 0.2433 0.01623 0.00678 -0.0096 0.7578 1.0000 2.000 0.2650 0.01644 0.00693 -0.0079 0.7256 1.0000 2.250 0.2870 0.01666 0.00708 -0.0062 0.6933 1.0000 2.500 0.3095 0.01690 0.00724 -0.0046 0.6609 1.0000 2.750 0.3323 0.01715 0.00744 -0.0031 0.6278 1.0000 3.000 0.3553 0.01742 0.00763 -0.0016 0.5943 1.0000 3.250 0.3788 0.01772 0.00787 -0.0004 0.5579 1.0000 3.500 0.4023 0.01804 0.00811 0.0009 0.5211 1.0000 3.750 0.4260 0.01840 0.00841 0.0020 0.4819 1.0000 4.000 0.4496 0.01880 0.00871 0.0031 0.4414 1.0000 4.250 0.4731 0.01926 0.00906 0.0041 0.3987 1.0000 4.500 0.4968 0.01981 0.00949 0.0049 0.3541 1.0000 4.750 0.5207 0.02046 0.01003 0.0055 0.3089 1.0000 5.000 0.5443 0.02123 0.01065 0.0060 0.2647 1.0000 5.250 0.5678 0.02213 0.01143 0.0065 0.2240 1.0000 5.500 0.5908 0.02319 0.01230 0.0069 0.1904 1.0000 5.750 0.6139 0.02432 0.01338 0.0074 0.1624 1.0000 6.000 0.6371 0.02554 0.01461 0.0079 0.1402 1.0000 6.250 0.6601 0.02685 0.01591 0.0085 0.1236 1.0000 6.500 0.6829 0.02820 0.01731 0.0090 0.1098 1.0000 6.750 0.7059 0.02975 0.01898 0.0096 0.0998 1.0000 7.000 0.7280 0.03128 0.02046 0.0102 0.0912 1.0000 7.250 0.7510 0.03312 0.02264 0.0107 0.0835 1.0000 7.500 0.7726 0.03497 0.02446 0.0112 0.0782 1.0000 7.750 0.7931 0.03727 0.02727 0.0117 0.0722 1.0000 8.000 0.8130 0.03947 0.02968 0.0122 0.0683 1.0000 8.250 0.8311 0.04218 0.03256 0.0125 0.0656 1.0000 8.500 0.8432 0.04582 0.03687 0.0128 0.0624 1.0000 8.750 0.8534 0.04922 0.04069 0.0128 0.0594 1.0000 9.000 0.8620 0.05259 0.04436 0.0128 0.0574 1.0000 9.250 0.8663 0.05643 0.04849 0.0126 0.0563 1.0000 9.500 0.8663 0.06054 0.05284 0.0121 0.0555 1.0000 9.750 0.8637 0.06468 0.05715 0.0114 0.0548 1.0000 10.000 0.8509 0.06950 0.06213 0.0100 0.0545 1.0000 10.250 0.7686 0.08643 0.07940 -0.0058 0.0583 1.0000