XFOIL Version 6.96 Calculated polar for: NACA 63(4)-421 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -18.500 -0.7336 0.11315 0.10672 -0.0553 1.0000 0.0540 -18.250 -0.7617 0.10440 0.09776 -0.0603 1.0000 0.0545 -18.000 -0.7548 0.10204 0.09543 -0.0614 1.0000 0.0556 -17.750 -0.7644 0.09690 0.09018 -0.0641 1.0000 0.0566 -17.500 -0.7768 0.09144 0.08457 -0.0670 1.0000 0.0575 -17.250 -0.7891 0.08617 0.07910 -0.0695 1.0000 0.0585 -17.000 -0.8006 0.08121 0.07393 -0.0719 1.0000 0.0596 -16.750 -0.8119 0.07647 0.06894 -0.0740 1.0000 0.0607 -16.500 -0.8006 0.07491 0.06745 -0.0743 1.0000 0.0620 -16.250 -0.7969 0.07238 0.06490 -0.0752 1.0000 0.0635 -16.000 -0.7958 0.06953 0.06194 -0.0761 1.0000 0.0650 -15.750 -0.7961 0.06652 0.05877 -0.0770 1.0000 0.0666 -15.500 -0.7923 0.06408 0.05622 -0.0776 1.0000 0.0682 -15.250 -0.7815 0.06255 0.05474 -0.0777 1.0000 0.0698 -15.000 -0.7732 0.06074 0.05290 -0.0778 1.0000 0.0715 -14.750 -0.7659 0.05882 0.05090 -0.0780 1.0000 0.0734 -14.500 -0.7590 0.05686 0.04879 -0.0782 1.0000 0.0754 -14.250 -0.7473 0.05558 0.04760 -0.0779 1.0000 0.0773 -14.000 -0.7377 0.05411 0.04615 -0.0778 1.0000 0.0795 -13.750 -0.7278 0.05266 0.04466 -0.0776 1.0000 0.0819 -13.500 -0.7177 0.05130 0.04324 -0.0772 1.0000 0.0845 -13.250 -0.7089 0.05000 0.04203 -0.0768 1.0000 0.0869 -13.000 -0.7014 0.04863 0.04070 -0.0763 1.0000 0.0900 -12.750 -0.6938 0.04741 0.03944 -0.0757 1.0000 0.0935 -12.500 -0.6906 0.04622 0.03837 -0.0746 1.0000 0.0964 -12.250 -0.6698 0.04452 0.03666 -0.0768 0.9759 0.1015 -12.000 -0.6465 0.04283 0.03497 -0.0797 0.9566 0.1077 -11.750 -0.6223 0.04114 0.03319 -0.0827 0.9412 0.1159 -11.500 -0.6023 0.03930 0.03138 -0.0854 0.9265 0.1242 -11.250 -0.5843 0.03762 0.02967 -0.0874 0.9124 0.1340 -11.000 -0.5701 0.03605 0.02806 -0.0885 0.8986 0.1451 -10.750 -0.5607 0.03461 0.02657 -0.0885 0.8848 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-0.0592 0.6444 0.5892 -1.000 0.1646 0.02234 0.01293 -0.0593 0.6414 0.5933 -0.750 0.1882 0.02243 0.01303 -0.0591 0.6363 0.5983 -0.500 0.2136 0.02237 0.01290 -0.0595 0.6311 0.6043 -0.250 0.2401 0.02241 0.01296 -0.0591 0.6269 0.6071 0.000 0.2686 0.02238 0.01291 -0.0592 0.6236 0.6106 0.250 0.2958 0.02243 0.01293 -0.0592 0.6199 0.6150 0.500 0.3181 0.02261 0.01315 -0.0589 0.6145 0.6205 0.750 0.3441 0.02266 0.01318 -0.0591 0.6102 0.6254 1.000 0.3709 0.02272 0.01327 -0.0589 0.6067 0.6286 1.250 0.4001 0.02272 0.01325 -0.0591 0.6038 0.6324 1.500 0.4244 0.02289 0.01345 -0.0589 0.5994 0.6372 1.750 0.4469 0.02312 0.01370 -0.0587 0.5939 0.6432 2.000 0.4722 0.02324 0.01386 -0.0584 0.5898 0.6473 2.250 0.4997 0.02331 0.01396 -0.0583 0.5866 0.6513 2.500 0.5300 0.02331 0.01394 -0.0588 0.5841 0.6559 2.750 0.5490 0.02371 0.01442 -0.0581 0.5786 0.6612 3.000 0.5713 0.02398 0.01474 -0.0577 0.5735 0.6665 3.250 0.5964 0.02412 0.01494 -0.0572 0.5697 0.6705 3.500 0.6257 0.02414 0.01498 -0.0574 0.5667 0.6755 3.750 0.6535 0.02425 0.01510 -0.0577 0.5632 0.6815 4.000 0.6672 0.02485 0.01581 -0.0563 0.5567 0.6870 4.250 0.6896 0.02506 0.01611 -0.0555 0.5523 0.6911 4.500 0.7184 0.02507 0.01615 -0.0557 0.5490 0.6963 4.750 0.7521 0.02500 0.01605 -0.0566 0.5463 0.7028 5.000 0.7581 0.02585 0.01709 -0.0542 0.5395 0.7084 5.250 0.7762 0.02622 0.01756 -0.0529 0.5346 0.7134 5.500 0.8044 0.02625 0.01763 -0.0530 0.5311 0.7193 5.750 0.8404 0.02611 0.01747 -0.0543 0.5282 0.7263 6.000 0.8398 0.02712 0.01868 -0.0508 0.5214 0.7313 6.250 0.8546 0.02757 0.01924 -0.0492 0.5160 0.7375 6.500 0.8855 0.02754 0.01924 -0.0498 0.5124 0.7447 6.750 0.9222 0.02724 0.01897 -0.0507 0.5095 0.7503 7.000 0.9008 0.02882 0.02076 -0.0448 0.5009 0.7571 7.250 0.9228 0.02899 0.02099 -0.0442 0.4959 0.7649 7.500 0.9633 0.02846 0.02050 -0.0455 0.4923 0.7710 7.750 0.9403 0.03022 0.02242 -0.0398 0.4834 0.7790 8.000 0.9646 0.03017 0.02242 -0.0394 0.4772 0.7869 8.250 1.0134 0.02897 0.02124 -0.0410 0.4730 0.7935 8.500 0.9751 0.03189 0.02434 -0.0350 0.4620 0.8037 8.750 1.0110 0.03110 0.02360 -0.0351 0.4573 0.8113 9.000 0.9941 0.03339 0.02603 -0.0318 0.4477 0.8216 9.250 1.0153 0.03333 0.02606 -0.0308 0.4412 0.8306 9.750 1.0250 0.03542 0.02836 -0.0272 0.4246 0.8528 10.000 1.0530 0.03483 0.02782 -0.0265 0.4181 0.8650 10.250 1.0364 0.03740 0.03055 -0.0238 0.4069 0.8804 10.500 1.0459 0.03804 0.03128 -0.0222 0.3981 0.8994 10.750 1.0491 0.03931 0.03267 -0.0208 0.3875 0.9293 11.000 1.0393 0.04204 0.03552 -0.0202 0.3745 1.0000 11.250 1.0554 0.04302 0.03652 -0.0204 0.3633 1.0000 11.500 1.0710 0.04397 0.03746 -0.0205 0.3512 1.0000 11.750 1.0708 0.04646 0.03999 -0.0205 0.3370 1.0000 12.000 1.0788 0.04816 0.04169 -0.0204 0.3229 1.0000 12.250 1.0898 0.04955 0.04303 -0.0203 0.3084 1.0000 12.500 1.0994 0.05106 0.04448 -0.0202 0.2929 1.0000 12.750 1.1060 0.05292 0.04628 -0.0201 0.2768 1.0000 13.000 1.1103 0.05510 0.04838 -0.0201 0.2607 1.0000 13.250 1.1132 0.05749 0.05071 -0.0201 0.2449 1.0000 13.500 1.1152 0.06005 0.05320 -0.0202 0.2298 1.0000 13.750 1.1168 0.06273 0.05582 -0.0204 0.2155 1.0000 14.250 1.1181 0.06857 0.06157 -0.0211 0.1895 1.0000 14.500 1.1191 0.07157 0.06455 -0.0217 0.1779 1.0000 14.750 1.1202 0.07459 0.06755 -0.0222 0.1673 1.0000 15.000 1.1212 0.07765 0.07054 -0.0228 0.1574 1.0000 15.250 1.1222 0.08088 0.07383 -0.0236 0.1477 1.0000 15.500 1.1237 0.08403 0.07698 -0.0244 0.1390 1.0000 15.750 1.1241 0.08737 0.08028 -0.0253 0.1308 1.0000 16.000 1.1257 0.09066 0.08363 -0.0262 0.1229 1.0000 16.250 1.1266 0.09400 0.08694 -0.0272 0.1161 1.0000 16.500 1.1279 0.09740 0.09040 -0.0284 0.1092 1.0000 16.750 1.1295 0.10074 0.09375 -0.0295 0.1033 1.0000