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 = 1.000 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -9.500 -0.3297 0.10269 0.10013 0.0082 0.6230 0.0047 -9.250 -0.3257 0.09897 0.09641 0.0067 0.6202 0.0047 -7.250 -0.3652 0.08114 0.07840 -0.0087 0.6072 0.0047 -6.750 -0.3498 0.07454 0.07174 -0.0122 0.6001 0.0047 -6.500 -0.3422 0.07060 0.06776 -0.0138 0.5967 0.0048 -6.250 -0.3327 0.06707 0.06420 -0.0149 0.5937 0.0049 -6.000 -0.3193 0.06372 0.06080 -0.0163 0.5902 0.0049 -5.750 -0.3063 0.06083 0.05787 -0.0171 0.5868 0.0050 -5.500 -0.2902 0.05749 0.05444 -0.0181 0.5835 0.0050 -5.250 -0.2735 0.05442 0.05130 -0.0189 0.5807 0.0050 -5.000 -0.2556 0.05141 0.04822 -0.0195 0.5777 0.0051 -4.750 -0.2367 0.04849 0.04521 -0.0198 0.5746 0.0052 -4.250 -0.1920 0.04175 0.03817 -0.0194 0.5687 0.0047 -4.000 -0.1750 0.03899 0.03530 -0.0191 0.5660 0.0044 -3.750 -0.1538 0.03621 0.03239 -0.0185 0.5631 0.0043 -3.500 -0.1320 0.03326 0.02928 -0.0175 0.5601 0.0042 -3.250 -0.1099 0.03033 0.02616 -0.0162 0.5571 0.0042 -3.000 -0.0876 0.02681 0.02238 -0.0142 0.5547 0.0045 -2.750 -0.0655 0.02334 0.01862 -0.0119 0.5524 0.0049 -2.500 -0.0426 0.02095 0.01600 -0.0103 0.5501 0.0049 -2.250 -0.0181 0.01965 0.01456 -0.0095 0.5475 0.0052 -2.000 0.0068 0.01836 0.01312 -0.0086 0.5448 0.0056 -1.750 0.0317 0.01638 0.01089 -0.0072 0.5421 0.0060 -1.500 0.0563 0.01189 0.00578 -0.0046 0.5398 0.0059 -1.250 0.0828 0.01038 0.00400 -0.0039 0.5374 0.0066 -1.000 0.1091 0.00975 0.00327 -0.0034 0.5352 0.0069 -0.750 0.1350 0.00927 0.00271 -0.0028 0.5328 0.0075 -0.500 0.1615 0.00904 0.00245 -0.0025 0.5301 0.0081 -0.250 0.1882 0.00887 0.00226 -0.0022 0.5274 0.0089 0.000 0.2147 0.00869 0.00203 -0.0019 0.5249 0.0097 0.250 0.2412 0.00851 0.00182 -0.0015 0.5227 0.0104 0.500 0.2674 0.00827 0.00156 -0.0011 0.5200 0.0117 0.750 0.2944 0.00817 0.00145 -0.0009 0.5161 0.0131 1.000 0.3214 0.00812 0.00137 -0.0007 0.5118 0.0150 1.250 0.3482 0.00803 0.00127 -0.0005 0.5083 0.0180 1.500 0.3754 0.00796 0.00122 -0.0003 0.5054 0.0234 1.750 0.4026 0.00791 0.00120 -0.0002 0.5025 0.0338 2.000 0.4298 0.00788 0.00118 -0.0001 0.4995 0.0438 2.250 0.4564 0.00780 0.00120 0.0001 0.4966 0.0919 2.500 0.4832 0.00775 0.00121 0.0003 0.4938 0.1320 3.000 0.5776 0.00602 0.00162 -0.0091 0.4856 0.9774 3.250 0.6228 0.00621 0.00175 -0.0130 0.4800 0.9832 3.500 0.6624 0.00632 0.00187 -0.0157 0.4747 0.9877 3.750 0.6945 0.00638 0.00190 -0.0168 0.4683 0.9885 4.000 0.7257 0.00645 0.00196 -0.0177 0.4625 0.9895 4.250 0.7572 0.00651 0.00202 -0.0187 0.4557 0.9906 4.500 0.7888 0.00660 0.00209 -0.0197 0.4492 0.9919 4.750 0.8222 0.00670 0.00220 -0.0211 0.4400 0.9939 5.000 0.8526 0.00682 0.00230 -0.0219 0.4271 0.9950 5.250 0.8803 0.00720 0.00246 -0.0224 0.3798 0.9955 5.500 0.9076 0.00783 0.00281 -0.0230 0.3199 0.9963 5.750 0.9348 0.00850 0.00322 -0.0237 0.2654 0.9971 6.000 0.9620 0.00895 0.00353 -0.0243 0.2325 0.9977 6.250 0.9898 0.00961 0.00397 -0.0251 0.1870 0.9986 6.500 1.0163 0.01033 0.00447 -0.0258 0.1434 0.9993 6.750 1.0441 0.01101 0.00497 -0.0268 0.1072 0.9999 7.000 1.0671 0.01161 0.00544 -0.0266 0.0825 1.0000 7.250 1.0888 0.01224 0.00596 -0.0262 0.0603 1.0000 7.500 1.1106 0.01280 0.00647 -0.0258 0.0444 1.0000 7.750 1.1311 0.01349 0.00706 -0.0253 0.0277 1.0000 8.000 1.1526 0.01401 0.00756 -0.0248 0.0219 1.0000 8.250 1.1741 0.01447 0.00804 -0.0243 0.0186 1.0000 8.500 1.1954 0.01492 0.00853 -0.0237 0.0174 1.0000 8.750 1.2159 0.01542 0.00908 -0.0231 0.0164 1.0000 9.000 1.2357 0.01596 0.00965 -0.0225 0.0157 1.0000 9.250 1.2542 0.01658 0.01031 -0.0218 0.0148 1.0000 9.500 1.2719 0.01727 0.01105 -0.0210 0.0141 1.0000 9.750 1.2868 0.01814 0.01199 -0.0202 0.0134 1.0000 10.000 1.2991 0.01911 0.01305 -0.0190 0.0130 1.0000 10.250 1.3057 0.02020 0.01422 -0.0171 0.0124 1.0000 10.500 1.3060 0.02112 0.01519 -0.0139 0.0123 1.0000 10.750 1.3128 0.02200 0.01612 -0.0120 0.0121 1.0000 11.000 1.3212 0.02295 0.01711 -0.0104 0.0118 1.0000 11.250 1.3292 0.02402 0.01824 -0.0090 0.0114 1.0000 11.500 1.3369 0.02521 0.01949 -0.0077 0.0112 1.0000 11.750 1.3450 0.02642 0.02075 -0.0066 0.0109 1.0000 12.000 1.3534 0.02765 0.02202 -0.0056 0.0102 1.0000 12.250 1.3609 0.02900 0.02344 -0.0046 0.0100 1.0000 12.500 1.3663 0.03055 0.02506 -0.0036 0.0097 1.0000 12.750 1.3735 0.03199 0.02652 -0.0028 0.0089 1.0000 13.000 1.3785 0.03365 0.02824 -0.0020 0.0085 1.0000 13.250 1.3817 0.03552 0.03018 -0.0012 0.0080 1.0000 13.500 1.3916 0.03680 0.03151 -0.0006 0.0077 1.0000 13.750 1.3981 0.03840 0.03319 0.0000 0.0073 1.0000 14.000 1.4047 0.04004 0.03489 0.0004 0.0066 1.0000 14.250 1.4105 0.04180 0.03662 0.0008 0.0046 1.0000 14.500 1.4140 0.04384 0.03871 0.0012 0.0042 1.0000 14.750 1.4155 0.04613 0.04106 0.0015 0.0035 1.0000 15.000 1.4156 0.04867 0.04366 0.0018 0.0027 1.0000 15.250 1.4146 0.05137 0.04643 0.0019 0.0022 1.0000 15.500 1.4151 0.05399 0.04914 0.0020 0.0021 1.0000 15.750 1.4168 0.05652 0.05176 0.0019 0.0021 1.0000 16.000 1.4108 0.06003 0.05536 0.0017 0.0015 1.0000 16.250 1.4097 0.06303 0.05845 0.0015 0.0016 1.0000 16.500 1.4089 0.06603 0.06154 0.0011 0.0015 1.0000 16.750 1.4064 0.06932 0.06493 0.0006 0.0014 1.0000 17.000 1.4032 0.07277 0.06848 0.0000 0.0013 1.0000 17.250 1.3977 0.07662 0.07245 -0.0007 0.0013 1.0000 17.500 1.3937 0.08035 0.07627 -0.0016 0.0012 1.0000 17.750 1.3890 0.08421 0.08024 -0.0025 0.0012 1.0000 18.000 1.3812 0.08861 0.08474 -0.0037 0.0010 1.0000 18.250 1.3749 0.09291 0.08915 -0.0050 0.0011 1.0000 18.500 1.3655 0.09781 0.09418 -0.0066 0.0011 1.0000 18.750 1.3563 0.10270 0.09915 -0.0083 0.0010 1.0000 19.000 1.3471 0.10772 0.10429 -0.0101 0.0010 1.0000 19.250 1.3355 0.11325 0.10994 -0.0122 0.0010 1.0000