XFOIL Version 6.96 Calculated polar for: MH 22 7.2% 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.250 -0.5192 0.08919 0.08704 0.0024 1.0000 0.0049 -8.000 -0.5215 0.08475 0.08264 0.0003 1.0000 0.0042 -6.500 -0.5042 0.05338 0.05117 -0.0215 1.0000 0.0023 -6.250 -0.4936 0.04653 0.04413 -0.0244 1.0000 0.0022 -6.000 -0.4804 0.03992 0.03728 -0.0259 1.0000 0.0021 -5.750 -0.4663 0.03310 0.03011 -0.0261 1.0000 0.0020 -5.500 -0.4488 0.02674 0.02325 -0.0258 0.9889 0.0019 -5.250 -0.4181 0.02141 0.01723 -0.0273 0.9433 0.0019 -5.000 -0.3928 0.01832 0.01355 -0.0268 0.9018 0.0019 -4.750 -0.3711 0.01620 0.01093 -0.0251 0.8671 0.0019 -4.500 -0.3481 0.01460 0.00891 -0.0238 0.8397 0.0020 -4.250 -0.3239 0.01338 0.00736 -0.0227 0.8171 0.0022 -4.000 -0.2985 0.01276 0.00646 -0.0220 0.7972 0.0024 -3.750 -0.2748 0.01132 0.00473 -0.0209 0.7796 0.0030 -3.500 -0.2492 0.01076 0.00401 -0.0204 0.7631 0.0036 -3.250 -0.2228 0.01054 0.00371 -0.0201 0.7484 0.0048 -3.000 -0.1962 0.01028 0.00336 -0.0197 0.7355 0.0061 -2.750 -0.1697 0.00986 0.00275 -0.0193 0.7238 0.0064 -2.500 -0.1426 0.00949 0.00216 -0.0187 0.7131 0.0085 -2.250 -0.1167 0.00897 0.00184 -0.0184 0.7033 0.0627 -2.000 -0.0906 0.00856 0.00166 -0.0182 0.6937 0.1296 -1.750 -0.0641 0.00828 0.00149 -0.0180 0.6850 0.1853 -1.500 -0.0376 0.00803 0.00136 -0.0178 0.6767 0.2422 -1.250 -0.0111 0.00776 0.00126 -0.0176 0.6684 0.3082 -1.000 0.0153 0.00752 0.00117 -0.0174 0.6606 0.3743 -0.750 0.0409 0.00716 0.00110 -0.0171 0.6525 0.4757 -0.500 0.0652 0.00671 0.00105 -0.0164 0.6446 0.6055 -0.250 0.0875 0.00624 0.00098 -0.0151 0.6369 0.7450 0.000 0.1128 0.00580 0.00101 -0.0141 0.6286 0.8944 0.500 0.2070 0.00588 0.00101 -0.0223 0.6088 0.9857 0.750 0.2445 0.00593 0.00100 -0.0244 0.5981 0.9960 1.000 0.2784 0.00596 0.00099 -0.0258 0.5864 1.0000 1.250 0.3043 0.00601 0.00099 -0.0253 0.5743 1.0000 1.500 0.3303 0.00608 0.00100 -0.0249 0.5605 1.0000 1.750 0.3561 0.00616 0.00102 -0.0245 0.5446 1.0000 2.000 0.3820 0.00625 0.00106 -0.0240 0.5254 1.0000 2.250 0.4078 0.00637 0.00113 -0.0236 0.5030 1.0000 2.500 0.4334 0.00652 0.00119 -0.0232 0.4778 1.0000 2.750 0.4590 0.00670 0.00127 -0.0227 0.4517 1.0000 3.000 0.4845 0.00690 0.00138 -0.0223 0.4261 1.0000 3.250 0.5101 0.00710 0.00151 -0.0219 0.4015 1.0000 3.500 0.5356 0.00731 0.00171 -0.0215 0.3765 1.0000 3.750 0.5611 0.00753 0.00187 -0.0211 0.3523 1.0000 4.000 0.5847 0.00808 0.00210 -0.0206 0.2816 1.0000 4.250 0.6051 0.00925 0.00254 -0.0199 0.1377 1.0000 4.500 0.6276 0.01004 0.00298 -0.0193 0.0645 1.0000 4.750 0.6495 0.01102 0.00362 -0.0186 0.0026 1.0000 5.000 0.6748 0.01134 0.00402 -0.0181 0.0018 1.0000 5.250 0.6997 0.01174 0.00453 -0.0175 0.0017 1.0000 5.500 0.7243 0.01223 0.00515 -0.0168 0.0016 1.0000 5.750 0.7481 0.01287 0.00601 -0.0161 0.0015 1.0000 6.000 0.7711 0.01368 0.00697 -0.0152 0.0015 1.0000 6.250 0.7930 0.01466 0.00809 -0.0142 0.0015 1.0000 6.500 0.8137 0.01585 0.00944 -0.0130 0.0015 1.0000 6.750 0.8337 0.01719 0.01094 -0.0118 0.0015 1.0000 7.000 0.8531 0.01876 0.01268 -0.0104 0.0016 1.0000 7.250 0.8722 0.02055 0.01467 -0.0091 0.0016 1.0000 7.500 0.8905 0.02270 0.01706 -0.0077 0.0016 1.0000 7.750 0.9076 0.02511 0.01976 -0.0062 0.0017 1.0000 8.000 0.9219 0.02805 0.02304 -0.0046 0.0017 1.0000 8.250 0.9326 0.03137 0.02674 -0.0029 0.0018 1.0000 8.500 0.9379 0.03520 0.03094 -0.0010 0.0018 1.0000 9.000 0.9499 0.04077 0.03697 0.0020 0.0021 1.0000 9.250 0.9530 0.04313 0.03953 0.0036 0.0021 1.0000 9.500 0.9530 0.04532 0.04190 0.0054 0.0022 1.0000 9.750 0.9463 0.04766 0.04441 0.0076 0.0023 1.0000 10.000 0.9310 0.05102 0.04793 0.0079 0.0023 1.0000 10.250 0.9172 0.05511 0.05217 0.0066 0.0023 1.0000 10.500 0.9035 0.06031 0.05757 0.0041 0.0024 1.0000 10.750 0.8874 0.06653 0.06393 0.0001 0.0024 1.0000 11.000 0.8719 0.07302 0.07050 -0.0054 0.0022 1.0000 11.250 0.8572 0.08133 0.07893 -0.0115 0.0023 1.0000