XFOIL Version 6.96 Calculated polar for: HQ 3.5/18 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.000 -0.7499 0.09119 0.08791 -0.0809 1.0000 0.0300 -17.750 -0.7948 0.07992 0.07638 -0.0880 1.0000 0.0300 -17.500 -0.8182 0.07274 0.06903 -0.0924 1.0000 0.0302 -17.250 -0.8348 0.06706 0.06319 -0.0958 1.0000 0.0305 -17.000 -0.8496 0.06205 0.05802 -0.0984 1.0000 0.0308 -16.750 -0.8617 0.05768 0.05349 -0.1005 1.0000 0.0310 -16.500 -0.8711 0.05392 0.04958 -0.1021 1.0000 0.0313 -16.250 -0.8787 0.05066 0.04618 -0.1032 1.0000 0.0315 -16.000 -0.8855 0.04766 0.04308 -0.1035 1.0000 0.0319 -15.750 -0.8846 0.04562 0.04105 -0.1033 1.0000 0.0324 -15.500 -0.8827 0.04385 0.03927 -0.1031 1.0000 0.0328 -15.250 -0.8821 0.04219 0.03759 -0.1026 1.0000 0.0332 -15.000 -0.8858 0.04049 0.03585 -0.1014 1.0000 0.0335 -14.500 -0.8745 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0.6720 0.6049 0.000 0.4711 0.00906 0.00343 -0.0993 0.6675 0.6116 0.250 0.4999 0.00911 0.00343 -0.0994 0.6633 0.6185 0.500 0.5278 0.00913 0.00345 -0.0994 0.6587 0.6228 0.750 0.5551 0.00912 0.00349 -0.0993 0.6532 0.6274 1.000 0.5829 0.00914 0.00349 -0.0992 0.6478 0.6329 1.250 0.6112 0.00920 0.00349 -0.0993 0.6426 0.6384 1.500 0.6378 0.00918 0.00355 -0.0990 0.6365 0.6435 1.750 0.6649 0.00921 0.00357 -0.0988 0.6300 0.6491 2.000 0.6921 0.00926 0.00359 -0.0987 0.6233 0.6555 2.250 0.7178 0.00926 0.00363 -0.0982 0.6144 0.6615 2.500 0.7437 0.00931 0.00368 -0.0978 0.6055 0.6687 2.750 0.7694 0.00937 0.00372 -0.0973 0.5957 0.6757 3.000 0.7944 0.00941 0.00378 -0.0968 0.5854 0.6813 3.250 0.8186 0.00949 0.00384 -0.0961 0.5735 0.6876 3.500 0.8421 0.00960 0.00390 -0.0952 0.5593 0.6941 3.750 0.8647 0.00970 0.00400 -0.0942 0.5443 0.7001 4.000 0.8872 0.00985 0.00412 -0.0932 0.5295 0.7076 4.250 0.9080 0.01002 0.00425 -0.0919 0.5133 0.7142 4.500 0.9273 0.01023 0.00441 -0.0903 0.4969 0.7206 4.750 0.9461 0.01049 0.00459 -0.0887 0.4815 0.7272 5.000 0.9644 0.01072 0.00479 -0.0870 0.4689 0.7330 5.500 0.9982 0.01119 0.00520 -0.0830 0.4467 0.7460 5.750 1.0131 0.01143 0.00545 -0.0807 0.4361 0.7521 6.000 1.0283 0.01173 0.00572 -0.0784 0.4249 0.7587 6.250 1.0452 0.01201 0.00600 -0.0766 0.4137 0.7652 6.500 1.0594 0.01233 0.00632 -0.0743 0.4024 0.7715 6.750 1.0743 0.01265 0.00664 -0.0722 0.3888 0.7785 7.000 1.0888 0.01299 0.00697 -0.0700 0.3723 0.7854 7.250 1.0995 0.01343 0.00738 -0.0674 0.3527 0.7929 7.500 1.1081 0.01402 0.00788 -0.0645 0.3352 0.8011 7.750 1.1172 0.01460 0.00844 -0.0618 0.3233 0.8096 8.000 1.1293 0.01515 0.00898 -0.0596 0.3141 0.8193 8.250 1.1394 0.01575 0.00959 -0.0572 0.3063 0.8307 8.500 1.1533 0.01622 0.01012 -0.0553 0.2998 0.8444 8.750 1.1657 0.01671 0.01070 -0.0533 0.2931 0.8649 9.000 1.1886 0.01723 0.01138 -0.0536 0.2856 0.9291 9.250 1.2110 0.01774 0.01192 -0.0537 0.2781 1.0000 9.500 1.2234 0.01854 0.01267 -0.0522 0.2708 1.0000 9.750 1.2411 0.01909 0.01325 -0.0513 0.2633 1.0000 10.000 1.2537 0.01991 0.01403 -0.0499 0.2553 1.0000 10.250 1.2695 0.02058 0.01472 -0.0488 0.2469 1.0000 10.500 1.2800 0.02154 0.01563 -0.0473 0.2372 1.0000 10.750 1.2945 0.02232 0.01642 -0.0462 0.2267 1.0000 11.000 1.3054 0.02332 0.01738 -0.0448 0.2160 1.0000 11.250 1.3134 0.02452 0.01852 -0.0433 0.2053 1.0000 11.500 1.3237 0.02562 0.01959 -0.0420 0.1955 1.0000 11.750 1.3322 0.02686 0.02080 -0.0406 0.1880 1.0000 12.000 1.3419 0.02806 0.02200 -0.0394 0.1818 1.0000 12.250 1.3482 0.02952 0.02342 -0.0380 0.1761 1.0000 12.500 1.3605 0.03059 0.02454 -0.0371 0.1723 1.0000 12.750 1.3711 0.03182 0.02579 -0.0361 0.1683 1.0000 13.000 1.3784 0.03331 0.02727 -0.0350 0.1642 1.0000 13.250 1.3863 0.03477 0.02874 -0.0339 0.1600 1.0000 13.500 1.3991 0.03591 0.02994 -0.0333 0.1571 1.0000 13.750 1.4100 0.03719 0.03127 -0.0326 0.1543 1.0000 14.000 1.4181 0.03874 0.03283 -0.0318 0.1513 1.0000 14.250 1.4241 0.04047 0.03455 -0.0309 0.1478 1.0000 14.500 1.4345 0.04188 0.03602 -0.0303 0.1451 1.0000 14.750 1.4466 0.04317 0.03740 -0.0299 0.1423 1.0000 15.000 1.4562 0.04470 0.03898 -0.0294 0.1392 1.0000 15.250 1.4630 0.04651 0.04080 -0.0289 0.1362 1.0000 15.500 1.4671 0.04857 0.04285 -0.0282 0.1326 1.0000 15.750 1.4788 0.05000 0.04439 -0.0280 0.1305 1.0000 16.000 1.4892 0.05157 0.04603 -0.0278 0.1277 1.0000 16.250 1.4960 0.05351 0.04801 -0.0276 0.1246 1.0000 16.500 1.5002 0.05573 0.05025 -0.0273 0.1215 1.0000 16.750 1.5055 0.05788 0.05246 -0.0272 0.1188 1.0000 17.000 1.5155 0.05962 0.05429 -0.0272 0.1154 1.0000 17.250 1.5209 0.06185 0.05657 -0.0272 0.1124 1.0000 17.500 1.5225 0.06454 0.05928 -0.0273 0.1089 1.0000 17.750 1.5266 0.06697 0.06178 -0.0274 0.1061 1.0000 18.000 1.5330 0.06921 0.06411 -0.0276 0.1029 1.0000 18.250 1.5348 0.07203 0.06697 -0.0280 0.0991 1.0000 18.500 1.5321 0.07543 0.07040 -0.0285 0.0957 1.0000 18.750 1.5368 0.07796 0.07303 -0.0289 0.0917 1.0000 19.000 1.5342 0.08149 0.07659 -0.0297 0.0872 1.0000 19.250 1.5323 0.08498 0.08014 -0.0305 0.0828 1.0000