XFOIL Version 6.96 Calculated polar for: NACA 11-H-09 AIRFOIL 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 ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3733 0.09262 0.08943 -0.0049 0.6510 0.0072 -7.750 -0.3735 0.08968 0.08650 -0.0062 0.6471 0.0072 -7.500 -0.3717 0.08676 0.08356 -0.0073 0.6432 0.0072 -7.250 -0.3655 0.08351 0.08028 -0.0091 0.6399 0.0072 -7.000 -0.3607 0.07934 0.07612 -0.0097 0.6366 0.0073 -6.750 -0.3518 0.07607 0.07280 -0.0116 0.6329 0.0073 -6.500 -0.3433 0.07274 0.06944 -0.0122 0.6294 0.0074 -6.250 -0.3327 0.06954 0.06619 -0.0134 0.6261 0.0075 -6.000 -0.3201 0.06630 0.06291 -0.0149 0.6228 0.0075 -5.750 -0.3067 0.06315 0.05971 -0.0160 0.6191 0.0077 -5.500 -0.2912 0.05998 0.05646 -0.0171 0.6154 0.0077 -5.250 -0.2749 0.05697 0.05336 -0.0180 0.6120 0.0079 -5.000 -0.2571 0.05388 0.05018 -0.0187 0.6086 0.0081 -4.750 -0.2381 0.05089 0.04710 -0.0193 0.6051 0.0083 -4.500 -0.2182 0.04796 0.04405 -0.0196 0.6018 0.0084 -4.250 -0.1975 0.04508 0.04104 -0.0196 0.5987 0.0089 -4.000 -0.1761 0.04228 0.03807 -0.0194 0.5959 0.0092 -3.750 -0.1495 0.03954 0.03514 -0.0189 0.5929 0.0102 -3.500 -0.1248 0.03681 0.03223 -0.0179 0.5898 0.0104 -3.000 -0.0866 0.03110 0.02618 -0.0162 0.5838 0.0084 -2.750 -0.0632 0.02829 0.02312 -0.0147 0.5810 0.0081 -2.500 -0.0393 0.02562 0.02019 -0.0131 0.5780 0.0079 -2.250 -0.0139 0.02412 0.01852 -0.0121 0.5749 0.0098 -2.000 0.0100 0.02200 0.01615 -0.0108 0.5722 0.0095 -1.750 0.0346 0.01987 0.01374 -0.0093 0.5696 0.0090 -1.500 0.0601 0.01770 0.01124 -0.0079 0.5673 0.0086 -1.250 0.0868 0.01563 0.00886 -0.0066 0.5648 0.0087 -1.000 0.1146 0.01378 0.00672 -0.0058 0.5619 0.0090 -0.750 0.1425 0.01244 0.00513 -0.0052 0.5589 0.0099 -0.500 0.1693 0.01183 0.00441 -0.0049 0.5562 0.0113 -0.250 0.1957 0.01132 0.00382 -0.0044 0.5538 0.0120 0.000 0.2217 0.01085 0.00329 -0.0039 0.5514 0.0127 0.250 0.2477 0.01047 0.00287 -0.0034 0.5486 0.0140 0.500 0.2738 0.01021 0.00258 -0.0030 0.5457 0.0152 0.750 0.2998 0.00999 0.00236 -0.0026 0.5431 0.0182 1.000 0.3262 0.00984 0.00217 -0.0022 0.5405 0.0206 1.250 0.3525 0.00971 0.00201 -0.0018 0.5378 0.0251 1.500 0.3794 0.00961 0.00192 -0.0016 0.5338 0.0337 1.750 0.4063 0.00953 0.00184 -0.0014 0.5294 0.0470 2.000 0.4322 0.00939 0.00182 -0.0011 0.5257 0.1171 2.500 0.5871 0.00779 0.00235 -0.0235 0.5179 0.9926 2.750 0.6453 0.00778 0.00229 -0.0304 0.5139 1.0000 3.000 0.6711 0.00783 0.00232 -0.0300 0.5106 1.0000 3.250 0.6969 0.00788 0.00236 -0.0297 0.5068 1.0000 3.500 0.7228 0.00793 0.00242 -0.0294 0.5022 1.0000 3.750 0.7486 0.00799 0.00247 -0.0291 0.4971 1.0000 4.000 0.7744 0.00805 0.00253 -0.0288 0.4920 1.0000 4.250 0.8003 0.00810 0.00261 -0.0285 0.4858 1.0000 4.750 0.8519 0.00824 0.00280 -0.0280 0.4741 1.0000 5.000 0.8776 0.00833 0.00290 -0.0277 0.4675 1.0000 5.250 0.9034 0.00841 0.00302 -0.0275 0.4599 1.0000 5.500 0.9289 0.00852 0.00315 -0.0272 0.4484 1.0000 5.750 0.9538 0.00871 0.00327 -0.0269 0.4226 1.0000 6.000 0.9774 0.00911 0.00350 -0.0265 0.3785 1.0000 6.250 0.9996 0.00976 0.00392 -0.0261 0.3297 1.0000 6.500 1.0215 0.01047 0.00445 -0.0258 0.2861 1.0000 6.750 1.0415 0.01148 0.00515 -0.0254 0.2246 1.0000 7.000 1.0622 0.01232 0.00578 -0.0250 0.1824 1.0000 7.250 1.0821 0.01321 0.00647 -0.0246 0.1423 1.0000 7.500 1.1018 0.01404 0.00717 -0.0241 0.1114 1.0000 7.750 1.1206 0.01492 0.00791 -0.0236 0.0832 1.0000 8.000 1.1386 0.01580 0.00869 -0.0229 0.0611 1.0000 8.250 1.1559 0.01667 0.00949 -0.0222 0.0431 1.0000 8.500 1.1718 0.01759 0.01036 -0.0213 0.0303 1.0000 8.750 1.1884 0.01839 0.01121 -0.0205 0.0252 1.0000 9.000 1.2039 0.01922 0.01208 -0.0197 0.0230 1.0000 9.250 1.2162 0.02023 0.01313 -0.0185 0.0209 1.0000 9.500 1.2256 0.02130 0.01427 -0.0170 0.0197 1.0000 9.750 1.2243 0.02248 0.01553 -0.0139 0.0188 1.0000 10.000 1.2276 0.02360 0.01672 -0.0116 0.0186 1.0000 10.250 1.2328 0.02481 0.01802 -0.0098 0.0184 1.0000 10.500 1.2383 0.02613 0.01944 -0.0082 0.0180 1.0000 10.750 1.2440 0.02753 0.02093 -0.0068 0.0177 1.0000 11.000 1.2490 0.02904 0.02253 -0.0055 0.0173 1.0000 11.250 1.2547 0.03056 0.02413 -0.0044 0.0168 1.0000 11.500 1.2597 0.03218 0.02584 -0.0033 0.0165 1.0000 11.750 1.2645 0.03386 0.02761 -0.0024 0.0162 1.0000 12.000 1.2693 0.03557 0.02939 -0.0015 0.0154 1.0000 12.250 1.2750 0.03723 0.03111 -0.0008 0.0147 1.0000 12.500 1.2767 0.03930 0.03326 0.0000 0.0143 1.0000 12.750 1.2787 0.04140 0.03542 0.0007 0.0135 1.0000 13.000 1.2761 0.04401 0.03814 0.0013 0.0127 1.0000 13.250 1.2788 0.04618 0.04039 0.0018 0.0123 1.0000 13.500 1.2874 0.04779 0.04209 0.0021 0.0120 1.0000 13.750 1.2899 0.05008 0.04449 0.0024 0.0117 1.0000 14.000 1.2987 0.05173 0.04622 0.0024 0.0110 1.0000 14.250 1.3018 0.05406 0.04865 0.0026 0.0106 1.0000 14.500 1.3074 0.05615 0.05082 0.0025 0.0099 1.0000 14.750 1.3117 0.05842 0.05317 0.0024 0.0094 1.0000 15.000 1.3136 0.06104 0.05586 0.0023 0.0089 1.0000 15.250 1.3138 0.06391 0.05882 0.0020 0.0086 1.0000 15.500 1.3184 0.06627 0.06124 0.0017 0.0076 1.0000 15.750 1.3183 0.06927 0.06437 0.0013 0.0073 1.0000 16.000 1.3228 0.07173 0.06694 0.0009 0.0061 1.0000 16.250 1.3238 0.07469 0.06998 0.0004 0.0055 1.0000 16.500 1.3232 0.07792 0.07327 -0.0004 0.0050 1.0000 16.750 1.3205 0.08151 0.07696 -0.0012 0.0044 1.0000 17.000 1.3170 0.08528 0.08082 -0.0021 0.0040 1.0000 17.250 1.3115 0.08942 0.08504 -0.0032 0.0036 1.0000 17.500 1.3059 0.09369 0.08942 -0.0045 0.0034 1.0000 17.750 1.2982 0.09838 0.09423 -0.0060 0.0034 1.0000 18.000 1.2890 0.10337 0.09931 -0.0077 0.0029 1.0000 18.250 1.2790 0.10867 0.10474 -0.0097 0.0029 1.0000 18.500 1.2659 0.11467 0.11087 -0.0120 0.0029 1.0000 18.750 1.2582 0.11971 0.11604 -0.0140 0.0027 1.0000 19.000 1.2468 0.12556 0.12202 -0.0165 0.0028 1.0000 19.250 1.2350 0.13162 0.12821 -0.0192 0.0027 1.0000