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 = 0.200 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -8.000 -0.3693 0.09619 0.09225 -0.0047 0.7056 0.0150 -7.750 -0.3694 0.09346 0.08951 -0.0066 0.7011 0.0150 -7.500 -0.3671 0.09067 0.08669 -0.0082 0.6973 0.0150 -7.250 -0.3602 0.08759 0.08360 -0.0106 0.6927 0.0151 -7.000 -0.3516 0.08441 0.08037 -0.0127 0.6885 0.0151 -6.750 -0.3414 0.08118 0.07705 -0.0143 0.6849 0.0151 -6.500 -0.3294 0.07790 0.07370 -0.0160 0.6810 0.0151 -6.250 -0.3161 0.07458 0.07031 -0.0175 0.6765 0.0152 -6.000 -0.3052 0.07054 0.06622 -0.0182 0.6727 0.0153 -5.750 -0.2986 0.06635 0.06201 -0.0177 0.6695 0.0157 -5.500 -0.2848 0.06314 0.05875 -0.0183 0.6653 0.0159 -5.250 -0.2699 0.06005 0.05560 -0.0190 0.6613 0.0163 -5.000 -0.2534 0.05703 0.05247 -0.0196 0.6579 0.0168 -4.750 -0.2353 0.05413 0.04942 -0.0201 0.6549 0.0173 -4.500 -0.2154 0.05126 0.04645 -0.0206 0.6511 0.0178 -4.250 -0.1941 0.04843 0.04345 -0.0208 0.6472 0.0189 -4.000 -0.1682 0.04605 0.04083 -0.0208 0.6437 0.0204 -3.750 -0.1373 0.04481 0.03920 -0.0200 0.6407 0.0213 -3.500 -0.1246 0.04014 0.03446 -0.0197 0.6373 0.0224 -3.250 -0.1060 0.03777 0.03202 -0.0194 0.6335 0.0236 -3.000 -0.0838 0.03558 0.02965 -0.0187 0.6303 0.0247 -2.750 -0.0603 0.03348 0.02733 -0.0178 0.6275 0.0260 -2.500 -0.0357 0.03155 0.02513 -0.0168 0.6249 0.0274 -2.250 -0.0036 0.03159 0.02477 -0.0154 0.6211 0.0305 -2.000 0.0205 0.02961 0.02254 -0.0143 0.6177 0.0306 -1.750 0.0409 0.02387 0.01642 -0.0123 0.6150 0.0163 -1.250 0.0936 0.02057 0.01250 -0.0103 0.6096 0.0166 -1.000 0.1206 0.01959 0.01135 -0.0099 0.6062 0.0183 -0.750 0.1488 0.01829 0.00978 -0.0093 0.6032 0.0188 -0.500 0.1772 0.01712 0.00836 -0.0088 0.6003 0.0191 -0.250 0.2055 0.01616 0.00719 -0.0084 0.5977 0.0199 0.000 0.2331 0.01549 0.00641 -0.0081 0.5948 0.0217 0.250 0.2594 0.01485 0.00581 -0.0078 0.5916 0.0247 0.500 0.2853 0.01434 0.00527 -0.0072 0.5885 0.0269 0.750 0.3111 0.01402 0.00488 -0.0067 0.5856 0.0302 1.000 0.3357 0.01360 0.00443 -0.0060 0.5831 0.0362 1.250 0.3616 0.01343 0.00417 -0.0055 0.5803 0.0434 1.500 0.3869 0.01320 0.00398 -0.0050 0.5768 0.0660 2.000 0.5608 0.01127 0.00404 -0.0308 0.5689 1.0000 2.250 0.5864 0.01135 0.00406 -0.0304 0.5647 1.0000 2.500 0.6121 0.01143 0.00412 -0.0301 0.5601 1.0000 2.750 0.6377 0.01150 0.00415 -0.0297 0.5564 1.0000 3.000 0.6632 0.01159 0.00418 -0.0293 0.5534 1.0000 3.250 0.6889 0.01171 0.00433 -0.0290 0.5492 1.0000 3.500 0.7145 0.01182 0.00446 -0.0287 0.5449 1.0000 3.750 0.7401 0.01191 0.00456 -0.0283 0.5411 1.0000 4.000 0.7655 0.01201 0.00464 -0.0279 0.5375 1.0000 4.250 0.7911 0.01214 0.00485 -0.0277 0.5319 1.0000 4.500 0.8164 0.01222 0.00496 -0.0273 0.5267 1.0000 4.750 0.8418 0.01232 0.00510 -0.0269 0.5213 1.0000 5.000 0.8671 0.01243 0.00529 -0.0266 0.5144 1.0000 5.250 0.8923 0.01251 0.00536 -0.0261 0.5086 1.0000 5.500 0.9175 0.01264 0.00562 -0.0259 0.5005 1.0000 5.750 0.9426 0.01274 0.00576 -0.0254 0.4942 1.0000 6.000 0.9677 0.01289 0.00605 -0.0252 0.4852 1.0000 6.250 0.9925 0.01300 0.00624 -0.0248 0.4750 1.0000 6.500 1.0171 0.01311 0.00645 -0.0244 0.4604 1.0000 6.750 1.0415 0.01325 0.00665 -0.0239 0.4420 1.0000 7.000 1.0650 0.01346 0.00686 -0.0235 0.4134 1.0000 7.250 1.0857 0.01398 0.00714 -0.0228 0.3608 1.0000 7.500 1.1024 0.01509 0.00791 -0.0221 0.2988 1.0000 7.750 1.1184 0.01626 0.00885 -0.0214 0.2488 1.0000 8.000 1.1336 0.01743 0.00984 -0.0206 0.2081 1.0000 8.250 1.1466 0.01871 0.01096 -0.0197 0.1691 1.0000 8.500 1.1563 0.02015 0.01222 -0.0185 0.1316 1.0000 8.750 1.1624 0.02176 0.01365 -0.0171 0.0986 1.0000 9.000 1.1663 0.02336 0.01517 -0.0154 0.0756 1.0000 9.250 1.1632 0.02497 0.01670 -0.0127 0.0600 1.0000 9.500 1.1619 0.02644 0.01816 -0.0101 0.0504 1.0000 9.750 1.1624 0.02803 0.01976 -0.0080 0.0424 1.0000 10.000 1.1631 0.02978 0.02151 -0.0063 0.0373 1.0000 10.250 1.1677 0.03132 0.02316 -0.0049 0.0348 1.0000 10.500 1.1713 0.03301 0.02495 -0.0036 0.0325 1.0000 10.750 1.1741 0.03485 0.02686 -0.0024 0.0307 1.0000 11.000 1.1754 0.03686 0.02895 -0.0013 0.0292 1.0000 11.250 1.1750 0.03910 0.03127 -0.0003 0.0280 1.0000 11.500 1.1746 0.04139 0.03368 0.0007 0.0273 1.0000 11.750 1.1773 0.04342 0.03583 0.0015 0.0269 1.0000 12.000 1.1801 0.04548 0.03802 0.0023 0.0262 1.0000 12.250 1.1826 0.04760 0.04025 0.0031 0.0258 1.0000 12.500 1.1853 0.04974 0.04251 0.0038 0.0249 1.0000 12.750 1.1891 0.05183 0.04471 0.0044 0.0243 1.0000 13.000 1.1930 0.05393 0.04693 0.0049 0.0234 1.0000 13.250 1.1965 0.05613 0.04924 0.0055 0.0228 1.0000 13.500 1.2000 0.05837 0.05159 0.0059 0.0221 1.0000 13.750 1.2030 0.06073 0.05405 0.0063 0.0213 1.0000 14.000 1.2049 0.06324 0.05668 0.0064 0.0205 1.0000 14.250 1.2056 0.06586 0.05937 0.0069 0.0195 1.0000 14.500 1.2070 0.06852 0.06216 0.0074 0.0186 1.0000 14.750 1.2084 0.07138 0.06521 0.0069 0.0179 1.0000 15.000 1.2085 0.07445 0.06847 0.0065 0.0171 1.0000 15.250 1.2076 0.07772 0.07191 0.0059 0.0162 1.0000 15.500 1.2054 0.08124 0.07558 0.0051 0.0153 1.0000 15.750 1.2025 0.08491 0.07940 0.0043 0.0148 1.0000 16.000 1.1987 0.08887 0.08346 0.0028 0.0139 1.0000 16.250 1.1933 0.09306 0.08774 0.0015 0.0133 1.0000 16.500 1.1855 0.09762 0.09240 0.0002 0.0126 1.0000 16.750 1.1771 0.10264 0.09760 -0.0015 0.0122 1.0000 17.000 1.1691 0.10779 0.10296 -0.0035 0.0119 1.0000 17.250 1.1585 0.11360 0.10899 -0.0060 0.0114 1.0000 17.500 1.1474 0.11960 0.11518 -0.0085 0.0112 1.0000 17.750 1.1347 0.12614 0.12191 -0.0116 0.0110 1.0000 18.000 1.1209 0.13320 0.12915 -0.0151 0.0108 1.0000 18.250 1.1059 0.14075 0.13686 -0.0190 0.0107 1.0000 18.500 1.0893 0.14913 0.14541 -0.0235 0.0105 1.0000 18.750 1.0716 0.15815 0.15457 -0.0285 0.0108 1.0000 19.000 1.0512 0.16853 0.16507 -0.0342 0.0110 1.0000 19.250 1.0256 0.18128 0.17790 -0.0411 0.0116 1.0000