XFOIL Version 6.96 Calculated polar for: NACA 2-H-15 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -11.000 -0.1135 0.09115 0.08809 -0.0902 0.6925 0.0228 -10.750 -0.1144 0.08763 0.08457 -0.0919 0.6917 0.0228 -10.500 -0.1128 0.08458 0.08152 -0.0932 0.6909 0.0229 -10.250 -0.1129 0.08133 0.07827 -0.0945 0.6901 0.0229 -10.000 -0.1139 0.07808 0.07504 -0.0958 0.6890 0.0229 -9.750 -0.1184 0.07440 0.07136 -0.0974 0.6879 0.0229 -9.500 -0.1341 0.06969 0.06668 -0.0986 0.6867 0.0232 -9.250 -0.1468 0.06605 0.06306 -0.1007 0.6857 0.0232 -9.000 -0.1578 0.06340 0.06043 -0.1006 0.6851 0.0233 -8.750 -0.1728 0.06062 0.05765 -0.0990 0.6842 0.0233 -8.500 -0.1878 0.05819 0.05521 -0.0963 0.6833 0.0234 -8.250 -0.2006 0.05625 0.05326 -0.0927 0.6822 0.0234 -8.000 -0.2120 0.05466 0.05165 -0.0884 0.6811 0.0235 -7.750 -0.2288 0.05296 0.04992 -0.0830 0.6800 0.0236 -7.500 -0.2346 0.05133 0.04825 -0.0793 0.6788 0.0237 -7.250 -0.2387 0.04948 0.04635 -0.0758 0.6777 0.0238 -7.000 -0.2392 0.04786 0.04467 -0.0725 0.6766 0.0241 -6.750 -0.2376 0.04623 0.04298 -0.0694 0.6757 0.0244 -6.500 -0.2387 0.04406 0.04071 -0.0656 0.6747 0.0245 -6.250 -0.2367 0.04214 0.03869 -0.0621 0.6737 0.0251 -6.000 -0.2394 0.03824 0.03441 -0.0557 0.6726 0.0272 -5.750 -0.2393 0.03624 0.03220 -0.0509 0.6711 0.0273 -5.500 -0.2356 0.03441 0.03021 -0.0467 0.6703 0.0273 -5.250 -0.2525 0.02979 0.02530 -0.0391 0.6695 0.0277 -5.000 -0.2403 0.02840 0.02386 -0.0366 0.6686 0.0279 -4.750 -0.2265 0.02724 0.02263 -0.0342 0.6675 0.0281 -4.500 -0.2119 0.02618 0.02150 -0.0319 0.6664 0.0283 -4.250 -0.1965 0.02515 0.02039 -0.0297 0.6652 0.0285 -4.000 -0.1803 0.02419 0.01934 -0.0275 0.6642 0.0289 -3.750 -0.1633 0.02319 0.01824 -0.0254 0.6631 0.0294 -3.500 -0.1450 0.02227 0.01720 -0.0235 0.6621 0.0301 -3.250 -0.1240 0.02233 0.01700 -0.0211 0.6611 0.0323 -3.000 -0.1070 0.02172 0.01618 -0.0185 0.6602 0.0325 -2.750 -0.0887 0.01825 0.01246 -0.0169 0.6593 0.0335 -2.500 -0.0628 0.01755 0.01176 -0.0168 0.6582 0.0342 -2.250 -0.0373 0.01690 0.01104 -0.0164 0.6570 0.0348 -2.000 -0.0118 0.01643 0.01049 -0.0159 0.6555 0.0361 -1.750 0.0424 0.01397 0.00770 -0.0211 0.6549 0.0309 -1.500 0.1094 0.01225 0.00588 -0.0298 0.6544 0.0294 -1.250 0.1476 0.01183 0.00547 -0.0323 0.6535 0.0301 -1.000 0.1911 0.01120 0.00484 -0.0359 0.6526 0.0301 -0.750 0.2274 0.01083 0.00447 -0.0380 0.6516 0.0305 -0.500 0.2584 0.01061 0.00426 -0.0388 0.6505 0.0314 -0.250 0.2896 0.01033 0.00398 -0.0397 0.6494 0.0315 0.000 0.3189 0.01014 0.00379 -0.0401 0.6482 0.0320 0.250 0.3471 0.01006 0.00372 -0.0403 0.6470 0.0325 0.500 0.3774 0.00977 0.00342 -0.0410 0.6461 0.0329 0.750 0.4073 0.00956 0.00321 -0.0416 0.6451 0.0337 1.000 0.4366 0.00943 0.00310 -0.0420 0.6441 0.0353 1.250 0.4658 0.00936 0.00303 -0.0425 0.6430 0.0365 1.500 0.4950 0.00932 0.00300 -0.0429 0.6417 0.0381 1.750 0.5239 0.00931 0.00300 -0.0434 0.6403 0.0396 2.000 0.5531 0.00925 0.00299 -0.0439 0.6394 0.0442 2.250 0.7515 0.00839 0.00463 -0.0829 0.6395 0.9195 2.500 0.7409 0.00906 0.00533 -0.0745 0.6382 0.9699 2.750 0.7776 0.00928 0.00555 -0.0766 0.6370 0.9741 3.000 0.8181 0.00936 0.00565 -0.0797 0.6357 0.9777 3.250 0.8734 0.00941 0.00571 -0.0859 0.6343 0.9859 3.500 0.9120 0.00925 0.00555 -0.0884 0.6318 0.9893 3.750 0.9500 0.00894 0.00522 -0.0908 0.6289 0.9913 4.000 0.9829 0.00916 0.00542 -0.0922 0.6266 0.9951 4.250 1.0188 0.00868 0.00498 -0.0942 0.6233 0.9963 4.500 1.0544 0.00831 0.00465 -0.0962 0.6186 0.9980 4.750 1.0873 0.00801 0.00428 -0.0974 0.6109 0.9993 5.000 1.1164 0.00791 0.00425 -0.0980 0.6037 0.9998 5.250 1.1435 0.00788 0.00419 -0.0981 0.5963 1.0000 6.500 1.2195 0.01520 0.01031 -0.0952 0.3150 1.0000 6.750 1.1908 0.01806 0.01301 -0.0882 0.2762 1.0000 7.000 1.1626 0.02009 0.01496 -0.0803 0.2560 1.0000 17.000 1.4295 0.08265 0.07746 -0.0269 0.0135 0.9999 17.250 1.4357 0.08469 0.07956 -0.0265 0.0134 0.9999 17.500 1.4434 0.08665 0.08160 -0.0264 0.0130 0.9999 17.750 1.4468 0.08902 0.08404 -0.0260 0.0129 0.9999 18.000 1.4520 0.09127 0.08636 -0.0257 0.0126 0.9999 18.250 1.4553 0.09373 0.08889 -0.0256 0.0125 0.9999 18.500 1.4600 0.09605 0.09127 -0.0255 0.0123 0.9998 18.750 1.4617 0.09874 0.09404 -0.0253 0.0121 0.9998 19.000 1.4654 0.10128 0.09662 -0.0255 0.0118 0.9998 19.250 1.4667 0.10409 0.09950 -0.0255 0.0117 0.9998