XFOIL Version 6.94 Calculated polar for: AH 80-136 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.080 Re = 0.450 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------- -------- --------- --------- -------- ------- ------- 0.000 0.1106 0.00932 0.00469 0.0070 0.5725 0.9599 0.500 0.2245 0.01015 0.00536 -0.0048 0.5657 0.9913 1.000 0.3087 0.01023 0.00536 -0.0111 0.5635 0.9989 1.500 0.3665 0.01016 0.00525 -0.0121 0.5602 1.0000 2.000 0.4192 0.01007 0.00511 -0.0119 0.5550 1.0000 2.500 0.4719 0.01005 0.00505 -0.0117 0.5499 1.0000 3.000 0.5245 0.01003 0.00497 -0.0113 0.5451 1.0000 3.500 0.5773 0.01005 0.00494 -0.0110 0.5406 1.0000 4.000 0.6304 0.01052 0.00541 -0.0110 0.5326 1.0000 4.500 0.6845 0.01053 0.00548 -0.0110 0.5295 1.0000 5.000 0.7389 0.01052 0.00554 -0.0110 0.5237 1.0000 5.500 0.7933 0.01053 0.00559 -0.0110 0.5171 1.0000 6.000 0.8478 0.01039 0.00552 -0.0108 0.5098 1.0000 6.500 0.9021 0.01053 0.00566 -0.0108 0.4993 1.0000 7.000 0.9585 0.01034 0.00563 -0.0112 0.4886 1.0000 7.500 1.0145 0.01023 0.00561 -0.0114 0.4743 1.0000 8.000 1.0709 0.01030 0.00578 -0.0121 0.4508 1.0000 8.500 1.1261 0.01077 0.00610 -0.0130 0.4010 1.0000 9.000 1.1748 0.01297 0.00781 -0.0153 0.2971 1.0000 9.500 1.2053 0.01821 0.01240 -0.0208 0.1709 1.0000 10.000 1.1976 0.02494 0.01867 -0.0228 0.0898 1.0000 10.500 1.1940 0.02997 0.02351 -0.0218 0.0543 1.0000 11.000 1.1992 0.03427 0.02778 -0.0209 0.0364 1.0000 11.500 1.1961 0.03930 0.03274 -0.0197 0.0192 1.0000 12.000 1.1975 0.04424 0.03775 -0.0189 0.0122 1.0000 12.500 1.1883 0.05059 0.04431 -0.0182 0.0095 1.0000 13.000 1.1967 0.05536 0.04924 -0.0181 0.0082 1.0000 13.500 1.1986 0.06101 0.05506 -0.0181 0.0068 1.0000 14.000 1.1951 0.06729 0.06156 -0.0182 0.0060 1.0000 14.500 1.1904 0.07387 0.06832 -0.0183 0.0056 1.0000 15.000 1.1887 0.08018 0.07484 -0.0184 0.0053 1.0000 15.500 1.1862 0.08670 0.08159 -0.0186 0.0052 1.0000 16.000 1.1867 0.09282 0.08795 -0.0188 0.0052 1.0000 16.500 1.1835 0.09952 0.09494 -0.0195 0.0052 1.0000 17.000 1.1743 0.10779 0.10353 -0.0212 0.0053 1.0000 17.500 1.1588 0.11775 0.11384 -0.0242 0.0055 1.0000 18.000 1.1325 0.13044 0.12696 -0.0292 0.0057 1.0000 18.500 1.0969 0.14607 0.14301 -0.0368 0.0061 1.0000 19.000 1.0549 0.16489 0.16221 -0.0473 0.0064 1.0000 19.500 0.9949 0.19239 0.19004 -0.0630 0.0068 1.0000 21.500 0.9496 0.27353 0.27109 -0.0927 0.0127 1.0000 22.000 0.9585 0.28352 0.28109 -0.0968 0.0118 1.0000 22.500 0.9679 0.29281 0.29042 -0.1006 0.0112 1.0000 23.000 0.9778 0.30153 0.29916 -0.1038 0.0107 1.0000 23.500 0.9863 0.31050 0.30815 -0.1068 0.0102 1.0000 25.000 0.9962 0.34936 0.34702 -0.1177 0.0096 1.0000 25.500 1.0002 0.36069 0.35837 -0.1210 0.0095 1.0000 26.000 1.0028 0.37191 0.36960 -0.1241 0.0095 1.0000 26.500 1.0033 0.38294 0.38065 -0.1268 0.0095 1.0000 27.000 1.0005 0.39355 0.39130 -0.1289 0.0094 1.0000 27.500 0.9903 0.40316 0.40095 -0.1299 0.0093 1.0000 29.500 0.7935 0.36894 0.36699 -0.1043 0.0070 1.0000 30.000 0.7860 0.36975 0.36783 -0.1049 0.0060 1.0000 30.500 0.7800 0.37035 0.36847 -0.1058 0.0053 1.0000 31.000 0.7750 0.37019 0.36834 -0.1066 0.0047 1.0000