XFOIL Version 6.96 Calculated polar for: GRUMMAN K-2 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 = 5.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.000 -1.0895 0.08171 0.07886 -0.0422 1.0000 0.0091 -15.750 -1.1251 0.07050 0.06743 -0.0492 1.0000 0.0091 -15.500 -1.1486 0.06242 0.05917 -0.0541 1.0000 0.0091 -15.250 -1.1656 0.05624 0.05282 -0.0574 1.0000 0.0091 -15.000 -1.1783 0.05133 0.04776 -0.0594 1.0000 0.0091 -14.750 -1.1885 0.04730 0.04358 -0.0605 1.0000 0.0091 -14.500 -1.1961 0.04393 0.04008 -0.0607 1.0000 0.0092 -14.250 -1.2015 0.04110 0.03712 -0.0604 1.0000 0.0092 -14.000 -1.2055 0.03860 0.03450 -0.0596 1.0000 0.0092 -13.750 -1.2078 0.03645 0.03224 -0.0584 1.0000 0.0093 -13.500 -1.2090 0.03456 0.03023 -0.0568 1.0000 0.0093 -13.250 -1.2094 0.03287 0.02844 -0.0550 1.0000 0.0093 -13.000 -1.2091 0.03137 0.02684 -0.0529 1.0000 0.0094 -12.750 -1.2087 0.03000 0.02538 -0.0504 1.0000 0.0094 -12.500 -1.2077 0.02879 0.02408 -0.0478 1.0000 0.0095 -12.250 -1.2068 0.02771 0.02291 -0.0448 1.0000 0.0095 -12.000 -1.2072 0.02673 0.02185 -0.0414 1.0000 0.0095 -11.750 -1.2104 0.02590 0.02094 -0.0373 1.0000 0.0096 -11.500 -1.1943 0.02484 0.01979 -0.0370 0.9990 0.0096 -11.250 -1.1737 0.02380 0.01866 -0.0373 0.9979 0.0097 -11.000 -1.1515 0.02283 0.01761 -0.0379 0.9969 0.0097 -10.750 -1.1282 0.02193 0.01662 -0.0385 0.9959 0.0098 -10.500 -1.1039 0.02113 0.01574 -0.0391 0.9952 0.0098 -10.250 -1.0798 0.02017 0.01470 -0.0398 0.9945 0.0099 -10.000 -1.0547 0.01925 0.01371 -0.0406 0.9939 0.0101 -9.750 -1.0324 0.01851 0.01291 -0.0405 0.9926 0.0102 -9.500 -1.0086 0.01786 0.01221 -0.0405 0.9914 0.0103 -9.250 -0.9837 0.01727 0.01159 -0.0407 0.9904 0.0105 -9.000 -0.9579 0.01673 0.01100 -0.0410 0.9894 0.0106 -8.750 -0.9310 0.01622 0.01045 -0.0415 0.9885 0.0108 -8.500 -0.9032 0.01573 0.00993 -0.0422 0.9877 0.0109 -8.250 -0.8743 0.01526 0.00943 -0.0430 0.9869 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0.9726 0.0278 -3.250 -0.2729 0.00927 0.00346 -0.0586 0.9723 0.0317 -3.000 -0.2404 0.00907 0.00331 -0.0598 0.9720 0.0367 -2.500 -0.1901 0.00869 0.00305 -0.0588 0.9665 0.0544 -2.250 -0.1587 0.00843 0.00291 -0.0598 0.9656 0.0766 -2.000 -0.1259 0.00805 0.00274 -0.0612 0.9648 0.1243 -1.750 -0.0911 0.00758 0.00257 -0.0632 0.9641 0.1955 -1.500 -0.0530 0.00706 0.00236 -0.0659 0.9631 0.2755 -1.250 -0.0081 0.00635 0.00202 -0.0700 0.9605 0.3723 -1.000 0.0320 0.00534 0.00161 -0.0734 0.9507 0.5369 -0.750 0.0723 0.00471 0.00144 -0.0763 0.9384 0.6700 -0.500 0.1105 0.00454 0.00125 -0.0782 0.9098 0.6869 -0.250 0.1419 0.00467 0.00112 -0.0786 0.8379 0.6970 0.000 0.1564 0.00564 0.00127 -0.0755 0.6319 0.7041 0.250 0.1800 0.00615 0.00139 -0.0746 0.5258 0.7104 0.500 0.2058 0.00655 0.00148 -0.0742 0.4440 0.7163 0.750 0.2322 0.00689 0.00159 -0.0739 0.3749 0.7224 1.000 0.2590 0.00721 0.00171 -0.0737 0.3190 0.7306 1.250 0.2861 0.00751 0.00182 -0.0735 0.2637 0.7373 1.500 0.3134 0.00775 0.00194 -0.0734 0.2244 0.7416 1.750 0.3410 0.00800 0.00204 -0.0733 0.1870 0.7447 2.000 0.3686 0.00826 0.00215 -0.0732 0.1514 0.7474 2.250 0.3960 0.00857 0.00227 -0.0731 0.1129 0.7498 2.500 0.4238 0.00879 0.00239 -0.0731 0.0917 0.7519 2.750 0.4515 0.00897 0.00252 -0.0730 0.0794 0.7538 3.000 0.4794 0.00915 0.00266 -0.0729 0.0694 0.7558 3.250 0.5069 0.00938 0.00280 -0.0728 0.0525 0.7578 3.500 0.5338 0.00972 0.00301 -0.0726 0.0306 0.7597 3.750 0.5614 0.00996 0.00321 -0.0725 0.0228 0.7617 4.000 0.5891 0.01021 0.00341 -0.0724 0.0164 0.7637 4.250 0.6168 0.01045 0.00361 -0.0723 0.0134 0.7655 4.500 0.6446 0.01067 0.00382 -0.0723 0.0119 0.7671 4.750 0.6721 0.01092 0.00407 -0.0721 0.0108 0.7687 5.000 0.6993 0.01116 0.00432 -0.0719 0.0101 0.7703 5.250 0.7265 0.01140 0.00458 -0.0717 0.0096 0.7718 5.500 0.7536 0.01167 0.00486 -0.0715 0.0091 0.7734 5.750 0.7805 0.01196 0.00516 -0.0712 0.0086 0.7750 6.000 0.8071 0.01232 0.00553 -0.0709 0.0082 0.7767 6.250 0.8338 0.01265 0.00589 -0.0706 0.0080 0.7782 6.500 0.8606 0.01297 0.00624 -0.0704 0.0078 0.7797 6.750 0.8872 0.01332 0.00661 -0.0701 0.0076 0.7814 7.000 0.9136 0.01370 0.00702 -0.0698 0.0074 0.7829 7.250 0.9399 0.01409 0.00744 -0.0695 0.0073 0.7843 7.500 0.9658 0.01451 0.00789 -0.0691 0.0071 0.7855 7.750 0.9914 0.01494 0.00838 -0.0686 0.0070 0.7868 8.000 1.0167 0.01538 0.00886 -0.0681 0.0069 0.7881 8.250 1.0419 0.01584 0.00936 -0.0676 0.0067 0.7896 8.500 1.0669 0.01631 0.00989 -0.0671 0.0066 0.7910 8.750 1.0917 0.01681 0.01043 -0.0666 0.0065 0.7925 9.000 1.1161 0.01734 0.01102 -0.0660 0.0064 0.7939 9.250 1.1400 0.01795 0.01168 -0.0653 0.0063 0.7952 9.500 1.1633 0.01860 0.01240 -0.0646 0.0062 0.7966 9.750 1.1858 0.01936 0.01324 -0.0637 0.0061 0.7980 10.000 1.2075 0.02022 0.01419 -0.0627 0.0061 0.7994 10.250 1.2283 0.02116 0.01524 -0.0616 0.0060 0.8008 10.500 1.2478 0.02225 0.01645 -0.0603 0.0060 0.8019 10.750 1.2675 0.02321 0.01753 -0.0590 0.0059 0.8032 11.000 1.2872 0.02411 0.01854 -0.0578 0.0059 0.8044 11.250 1.3061 0.02506 0.01961 -0.0565 0.0059 0.8057 11.500 1.3241 0.02606 0.02074 -0.0551 0.0059 0.8069 11.750 1.3408 0.02716 0.02197 -0.0535 0.0059 0.8082 12.000 1.3562 0.02834 0.02328 -0.0518 0.0059 0.8097 12.250 1.3706 0.02955 0.02463 -0.0499 0.0058 0.8112 12.500 1.3832 0.03085 0.02607 -0.0479 0.0058 0.8126 12.750 1.3932 0.03231 0.02768 -0.0456 0.0058 0.8140 13.000 1.4020 0.03373 0.02924 -0.0432 0.0058 0.8154 13.250 1.4036 0.03536 0.03104 -0.0397 0.0058 0.8167 13.500 1.4014 0.03710 0.03292 -0.0359 0.0058 0.8180 13.750 1.3979 0.03903 0.03501 -0.0324 0.0058 0.8191 14.000 1.3911 0.04131 0.03746 -0.0290 0.0058 0.8206 14.250 1.3812 0.04404 0.04037 -0.0261 0.0058 0.8221 14.500 1.3701 0.04718 0.04368 -0.0241 0.0057 0.8236 14.750 1.3546 0.05126 0.04795 -0.0233 0.0057 0.8249 15.000 1.3314 0.05736 0.05426 -0.0250 0.0057 0.8262 15.250 1.2975 0.06879 0.06597 -0.0339 0.0058 0.8272 15.500 1.1957 0.10011 0.09770 -0.0557 0.0058 0.8272