XFOIL Version 6.96 Calculated polar for: GOE 15K 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 ------ -------- --------- --------- -------- -------- -------- -18.500 -0.6322 0.09604 0.09329 -0.1326 0.9696 0.0086 -18.250 -0.7126 0.07994 0.07696 -0.1408 0.9692 0.0083 -18.000 -0.7733 0.06717 0.06395 -0.1480 0.9687 0.0081 -17.750 -0.8153 0.05691 0.05349 -0.1547 0.9683 0.0079 -17.500 -0.8487 0.04739 0.04374 -0.1622 0.9679 0.0077 -17.250 -0.8829 0.04268 0.03890 -0.1604 0.9626 0.0079 -17.000 -0.8884 0.03904 0.03513 -0.1623 0.9609 0.0079 -16.750 -0.8991 0.03524 0.03119 -0.1637 0.9596 0.0082 -16.500 -0.9001 0.03273 0.02855 -0.1640 0.9586 0.0078 -16.250 -0.8978 0.03065 0.02637 -0.1639 0.9578 0.0082 -16.000 -0.8914 0.02899 0.02464 -0.1637 0.9572 0.0088 -15.750 -0.9119 0.02781 0.02335 -0.1569 0.9503 0.0085 -15.500 -0.9080 0.02642 0.02187 -0.1551 0.9483 0.0087 -15.250 -0.8986 0.02527 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-0.1028 0.8096 0.2817 -0.750 0.3146 0.00799 0.00241 -0.0994 0.8066 0.3082 -0.500 0.3336 0.00793 0.00243 -0.0976 0.8045 0.3329 -0.250 0.3529 0.00788 0.00245 -0.0958 0.8021 0.3546 0.000 0.3745 0.00778 0.00245 -0.0946 0.7994 0.3856 0.250 0.4000 0.00768 0.00245 -0.0943 0.7975 0.4171 0.500 0.4297 0.00763 0.00243 -0.0950 0.7947 0.4334 0.750 0.4397 0.00752 0.00251 -0.0911 0.7922 0.4833 1.000 0.4546 0.00733 0.00256 -0.0884 0.7900 0.5552 1.250 0.4399 0.00662 0.00259 -0.0788 0.7861 0.7737 1.750 0.6343 0.00763 0.00407 -0.1111 0.7798 0.9245 2.000 0.6440 0.00795 0.00442 -0.1069 0.7722 0.9373 2.250 0.6568 0.00810 0.00455 -0.1035 0.7662 0.9436 2.500 0.6840 0.00826 0.00472 -0.1036 0.7608 0.9458 2.750 0.6934 0.00854 0.00497 -0.0994 0.7470 0.9515 3.000 0.6994 0.00882 0.00521 -0.0945 0.7269 0.9556 3.250 0.7117 0.00920 0.00548 -0.0912 0.6929 0.9577 3.500 0.6848 0.01020 0.00621 -0.0790 0.6371 0.9656 3.750 0.6859 0.01118 0.00691 -0.0737 0.5773 0.9673 4.000 0.6760 0.01241 0.00777 -0.0663 0.4895 0.9697 4.250 0.6680 0.01366 0.00868 -0.0594 0.4175 0.9740 4.500 0.6784 0.01423 0.00915 -0.0561 0.3941 0.9763 4.750 0.7035 0.01460 0.00945 -0.0562 0.3723 0.9770 5.000 0.7302 0.01507 0.00980 -0.0568 0.3450 0.9783 5.250 0.7521 0.01550 0.01014 -0.0562 0.3196 0.9795 5.500 0.7655 0.01619 0.01065 -0.0539 0.2769 0.9812 5.750 0.7749 0.01702 0.01126 -0.0509 0.2325 0.9836 6.000 0.7872 0.01763 0.01179 -0.0482 0.2116 0.9856 6.250 0.8066 0.01809 0.01213 -0.0473 0.1853 0.9861 6.500 0.8257 0.01853 0.01247 -0.0463 0.1620 0.9866 6.750 0.8428 0.01901 0.01283 -0.0449 0.1384 0.9870 7.000 0.8659 0.01925 0.01308 -0.0445 0.1351 0.9875 7.250 0.8806 0.01992 0.01355 -0.0428 0.1002 0.9882 7.500 0.8996 0.02031 0.01392 -0.0417 0.0917 0.9887 7.750 0.9164 0.02079 0.01432 -0.0403 0.0785 0.9892 8.250 0.9529 0.02159 0.01509 -0.0378 0.0666 0.9902 8.500 0.9719 0.02198 0.01548 -0.0367 0.0640 0.9908 8.750 0.9891 0.02248 0.01595 -0.0355 0.0563 0.9915 9.000 1.0067 0.02290 0.01637 -0.0341 0.0543 0.9919 9.250 1.0232 0.02336 0.01683 -0.0326 0.0506 0.9923 9.500 1.0407 0.02377 0.01727 -0.0313 0.0486 0.9927 9.750 1.0556 0.02438 0.01783 -0.0296 0.0409 0.9933 10.000 1.0717 0.02507 0.01850 -0.0281 0.0357 0.9944 10.250 1.0871 0.02561 0.01902 -0.0266 0.0296 0.9946 10.500 1.1021 0.02619 0.01956 -0.0251 0.0245 0.9947 10.750 1.1181 0.02672 0.02010 -0.0237 0.0224 0.9948 11.000 1.1328 0.02733 0.02071 -0.0222 0.0200 0.9950 11.250 1.1481 0.02790 0.02130 -0.0208 0.0182 0.9951 11.500 1.1625 0.02854 0.02196 -0.0192 0.0169 0.9953 11.750 1.1774 0.02915 0.02260 -0.0178 0.0162 0.9954 12.000 1.1925 0.02975 0.02322 -0.0164 0.0152 0.9956 12.250 1.2063 0.03043 0.02394 -0.0149 0.0145 0.9957 12.500 1.2190 0.03117 0.02468 -0.0132 0.0131 0.9958 12.750 1.2328 0.03186 0.02542 -0.0117 0.0129 0.9959 13.000 1.2469 0.03263 0.02622 -0.0104 0.0118 0.9962 13.250 1.2623 0.03337 0.02700 -0.0094 0.0117 0.9966 13.500 1.2738 0.03424 0.02790 -0.0077 0.0110 0.9967 13.750 1.2844 0.03513 0.02883 -0.0059 0.0103 0.9967 14.000 1.2949 0.03603 0.02978 -0.0042 0.0103 0.9967 14.250 1.3067 0.03685 0.03063 -0.0026 0.0098 0.9968 14.500 1.3165 0.03781 0.03164 -0.0008 0.0094 0.9968 14.750 1.3251 0.03884 0.03274 0.0011 0.0095 0.9967 15.000 1.3326 0.04000 0.03394 0.0031 0.0089 0.9967 15.250 1.3411 0.04107 0.03506 0.0049 0.0087 0.9966 15.500 1.3473 0.04233 0.03638 0.0069 0.0086 0.9965 15.750 1.3566 0.04334 0.03743 0.0084 0.0079 0.9965 16.000 1.3605 0.04481 0.03898 0.0106 0.0079 0.9964 16.250 1.3667 0.04610 0.04034 0.0124 0.0077 0.9963 16.500 1.3745 0.04725 0.04151 0.0139 0.0072 0.9962 16.750 1.3753 0.04904 0.04340 0.0161 0.0073 0.9960 17.000 1.3796 0.05054 0.04492 0.0179 0.0064 0.9959 17.250 1.3842 0.05205 0.04654 0.0195 0.0070 0.9958 17.500 1.3849 0.05397 0.04853 0.0213 0.0069 0.9957 17.750 1.3853 0.05594 0.05055 0.0229 0.0066 0.9956 18.000 1.3874 0.05782 0.05253 0.0243 0.0068 0.9956 18.250 1.3874 0.06001 0.05479 0.0257 0.0063 0.9955 18.500 1.3867 0.06253 0.05741 0.0265 0.0066 0.9957 18.750 1.3907 0.06459 0.05954 0.0269 0.0062 0.9958 19.000 1.3887 0.06714 0.06218 0.0279 0.0062 0.9957 19.250 1.3834 0.07008 0.06523 0.0289 0.0062 0.9957