XFOIL Version 6.96 Calculated polar for: GRUMMAN K-3 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.7811 0.08871 0.08194 -0.0673 0.9999 0.1306 -13.750 -0.8815 0.07448 0.06748 -0.0711 0.9999 0.1291 -13.500 -0.9505 0.06681 0.05959 -0.0706 0.9999 0.1283 -13.250 -1.0037 0.06198 0.05456 -0.0679 0.9999 0.1280 -13.000 -1.0498 0.05876 0.05118 -0.0634 0.9999 0.1279 -12.750 -1.0848 0.05552 0.04771 -0.0603 0.9999 0.1285 -12.500 -1.1081 0.05222 0.04408 -0.0580 0.9999 0.1297 -12.250 -1.1168 0.04935 0.04092 -0.0564 0.9999 0.1314 -12.000 -1.0992 0.04843 0.04014 -0.0552 0.9999 0.1339 -11.750 -1.0896 0.04703 0.03868 -0.0540 0.9999 0.1367 -11.500 -1.0866 0.04480 0.03614 -0.0531 0.9999 0.1398 -11.250 -1.0769 0.04283 0.03397 -0.0525 0.9999 0.1430 -11.000 -1.0596 0.04191 0.03314 -0.0516 0.9999 0.1463 -10.750 -1.0455 0.04046 0.03151 -0.0511 0.9999 0.1504 -10.500 -1.0298 0.03887 0.02976 -0.0509 0.9999 0.1546 -10.250 -1.0109 0.03804 0.02900 -0.0502 0.9999 0.1588 -10.000 -0.9927 0.03667 0.02733 -0.0504 0.9999 0.1643 -9.750 -0.9728 0.03576 0.02658 -0.0498 0.9999 0.1690 -9.500 -0.9522 0.03479 0.02548 -0.0498 0.9999 0.1752 -9.250 -0.9312 0.03377 0.02449 -0.0496 0.9999 0.1810 -9.000 -0.9093 0.03299 0.02368 -0.0497 0.9999 0.1880 -8.750 -0.8872 0.03207 0.02277 -0.0496 0.9999 0.1951 -8.500 -0.8640 0.03135 0.02202 -0.0498 0.9999 0.2034 -8.250 -0.8411 0.03056 0.02132 -0.0498 0.9999 0.2115 -8.000 -0.8159 0.02989 0.02051 -0.0505 0.9999 0.2216 -7.750 -0.7930 0.02924 0.02007 -0.0503 0.9999 0.2306 -7.500 -0.7675 0.02857 0.01939 -0.0509 0.9999 0.2418 -7.250 -0.7420 0.02804 0.01891 -0.0514 0.9999 0.2538 -7.000 -0.7169 0.02749 0.01851 -0.0517 0.9999 0.2660 -6.750 -0.6903 0.02696 0.01808 -0.0523 0.9999 0.2803 -6.500 -0.6631 0.02649 0.01771 -0.0531 0.9999 0.2969 -6.250 -0.6356 0.02608 0.01747 -0.0539 0.9999 0.3159 -6.000 -0.6079 0.02576 0.01740 -0.0547 0.9999 0.3384 -5.750 -0.5795 0.02558 0.01742 -0.0556 0.9999 0.3666 -5.500 -0.5532 0.02565 0.01777 -0.0557 0.9999 0.3959 -5.250 -0.5268 0.02592 0.01817 -0.0558 0.9999 0.4285 -5.000 -0.5055 0.02651 0.01893 -0.0544 0.9999 0.4524 -4.750 -0.4847 0.02719 0.01969 -0.0528 0.9999 0.4734 -4.500 -0.4637 0.02789 0.02043 -0.0514 0.9999 0.4924 -4.250 -0.4413 0.02857 0.02109 -0.0504 0.9999 0.5106 -4.000 -0.4287 0.02952 0.02219 -0.0464 0.9999 0.5186 -3.750 -0.4061 0.03014 0.02277 -0.0456 0.9999 0.5343 -3.500 -0.3930 0.03104 0.02378 -0.0419 0.9999 0.5419 -3.250 -0.3691 0.03154 0.02423 -0.0416 0.9999 0.5564 -3.000 -0.3565 0.03237 0.02516 -0.0378 0.9999 0.5630 -2.750 -0.3297 0.03277 0.02549 -0.0385 0.9999 0.5779 -2.500 -0.3185 0.03352 0.02634 -0.0345 0.9999 0.5834 -2.250 -0.3018 0.03414 0.02700 -0.0322 0.9999 0.5923 -2.000 -0.2775 0.03448 0.02732 -0.0323 0.9999 0.6039 -1.750 -0.2650 0.03511 0.02803 -0.0289 0.9999 0.6102 -1.500 -0.2336 0.03543 0.02827 -0.0313 0.9999 0.6246 -1.250 -0.2235 0.03593 0.02888 -0.0274 0.9999 0.6296 -1.000 -0.2086 0.03646 0.02947 -0.0250 0.9999 0.6371 -0.750 -0.1777 0.03677 0.02974 -0.0275 0.9999 0.6493 -0.500 -0.1670 0.03723 0.03030 -0.0241 0.9999 0.6546 -0.250 -0.1489 0.03773 0.03085 -0.0230 0.9999 0.6631 0.000 -0.1226 0.03816 0.03129 -0.0243 0.9999 0.6735 0.250 -0.0310 0.04028 0.03345 -0.0339 0.9621 0.6855 0.500 0.0222 0.04068 0.03385 -0.0397 0.9473 0.6956 0.750 0.0558 0.04095 0.03420 -0.0401 0.9341 0.7014 1.000 0.1022 0.04117 0.03445 -0.0437 0.9214 0.7090 1.250 0.1685 0.04117 0.03447 -0.0514 0.9089 0.7170 1.500 0.2024 0.04032 0.03370 -0.0510 0.8870 0.7215 1.750 0.2575 0.03916 0.03260 -0.0542 0.8664 0.7275 2.000 0.3180 0.03813 0.03163 -0.0594 0.8528 0.7341 2.250 0.3723 0.03701 0.03059 -0.0632 0.8412 0.7396 2.500 0.4031 0.03616 0.02986 -0.0627 0.8264 0.7435 2.750 0.4484 0.03490 0.02871 -0.0643 0.8143 0.7486 3.000 0.5048 0.03313 0.02707 -0.0677 0.8024 0.7547 3.250 0.5508 0.03155 0.02561 -0.0697 0.7851 0.7596 3.500 0.5844 0.02981 0.02402 -0.0683 0.7670 0.7633 3.750 0.6200 0.02782 0.02217 -0.0669 0.7443 0.7681 4.000 0.6499 0.02633 0.02078 -0.0653 0.7008 0.7735 4.250 0.7229 0.02406 0.01666 -0.0680 0.4079 0.7786 4.500 0.7333 0.02537 0.01721 -0.0652 0.3226 0.7819 4.750 0.7516 0.02628 0.01772 -0.0635 0.2845 0.7857 5.000 0.7764 0.02704 0.01829 -0.0631 0.2589 0.7906 5.250 0.8081 0.02787 0.01893 -0.0642 0.2388 0.7961 5.500 0.8427 0.02873 0.01962 -0.0659 0.2219 0.8009 5.750 0.8730 0.02956 0.02026 -0.0664 0.2076 0.8051 6.000 0.8961 0.03008 0.02087 -0.0656 0.1951 0.8098 6.250 0.9276 0.03098 0.02172 -0.0667 0.1821 0.8154 6.500 0.9597 0.03195 0.02259 -0.0679 0.1699 0.8210 6.750 0.9818 0.03262 0.02320 -0.0669 0.1594 0.8263 7.000 1.0050 0.03345 0.02413 -0.0663 0.1486 0.8320 7.250 1.0341 0.03455 0.02521 -0.0671 0.1373 0.8377 7.500 1.0566 0.03548 0.02607 -0.0663 0.1280 0.8428 7.750 1.0793 0.03639 0.02688 -0.0657 0.1191 0.8493 8.000 1.0998 0.03744 0.02811 -0.0648 0.1103 0.8564 8.250 1.1165 0.03849 0.02927 -0.0628 0.1032 0.8629 8.500 1.1409 0.03970 0.03041 -0.0626 0.0971 0.8705 8.750 1.1580 0.04080 0.03167 -0.0610 0.0915 0.8774 9.000 1.1742 0.04212 0.03314 -0.0593 0.0869 0.8852 9.250 1.1923 0.04321 0.03428 -0.0580 0.0829 0.8939 9.500 1.2080 0.04494 0.03620 -0.0562 0.0799 0.9039 9.750 1.2151 0.04653 0.03809 -0.0530 0.0772 0.9148 10.000 1.2327 0.04755 0.03908 -0.0516 0.0749 0.9282 10.250 1.2363 0.04941 0.04122 -0.0482 0.0730 0.9439 10.500 1.2318 0.05146 0.04370 -0.0441 0.0712 0.9660 10.750 1.2420 0.05330 0.04572 -0.0429 0.0692 1.0001 11.000 1.2746 0.05526 0.04753 -0.0452 0.0671 1.0001 11.250 1.2624 0.05915 0.05198 -0.0420 0.0665 1.0001 11.500 1.2487 0.06337 0.05665 -0.0393 0.0660 1.0001 11.750 1.2296 0.06796 0.06167 -0.0368 0.0658 1.0001 12.000 1.2064 0.07299 0.06708 -0.0348 0.0657 1.0001 12.250 1.1774 0.07870 0.07314 -0.0336 0.0659 1.0001 12.500 1.1459 0.08506 0.07983 -0.0335 0.0662 1.0001 12.750 1.1123 0.09224 0.08729 -0.0349 0.0665 1.0001 13.000 1.0813 0.10002 0.09528 -0.0378 0.0669 1.0001