XFOIL Version 6.96 Calculated polar for: USA 28 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 ------ -------- --------- --------- -------- -------- -------- -16.750 -0.9259 0.08460 0.08182 -0.0587 1.0000 0.0092 -16.500 -0.9575 0.07663 0.07375 -0.0627 1.0000 0.0093 -16.250 -0.9879 0.06927 0.06628 -0.0663 1.0000 0.0091 -16.000 -1.0278 0.06114 0.05803 -0.0702 1.0000 0.0089 -15.750 -1.0680 0.05355 0.05031 -0.0736 1.0000 0.0088 -15.500 -1.1212 0.04487 0.04150 -0.0775 1.0000 0.0086 -15.250 -1.1671 0.03267 0.02898 -0.0900 0.9989 0.0083 -15.000 -1.1643 0.02946 0.02559 -0.0922 0.9966 0.0085 -14.750 -1.1556 0.02757 0.02358 -0.0924 0.9945 0.0088 -14.500 -1.1449 0.02597 0.02189 -0.0918 0.9922 0.0093 -14.250 -1.1301 0.02463 0.02044 -0.0914 0.9900 0.0097 -14.000 -1.1112 0.02345 0.01918 -0.0915 0.9882 0.0103 -13.750 -1.0887 0.02242 0.01806 -0.0919 0.9868 0.0107 -13.500 -1.0635 0.02147 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0.4528 0.00799 0.00147 -0.0746 0.4705 0.3379 1.500 0.4729 0.00815 0.00155 -0.0729 0.4491 0.3442 1.750 0.4946 0.00827 0.00163 -0.0715 0.4368 0.3498 2.000 0.5163 0.00838 0.00171 -0.0702 0.4273 0.3549 2.250 0.5393 0.00844 0.00177 -0.0691 0.4212 0.3594 2.500 0.5621 0.00852 0.00184 -0.0680 0.4154 0.3633 2.750 0.5844 0.00860 0.00192 -0.0667 0.4106 0.3675 3.000 0.6077 0.00865 0.00200 -0.0657 0.4069 0.3713 3.250 0.6310 0.00871 0.00207 -0.0647 0.4029 0.3747 3.500 0.6538 0.00880 0.00216 -0.0636 0.3990 0.3777 3.750 0.6759 0.00891 0.00226 -0.0624 0.3945 0.3807 4.000 0.6989 0.00896 0.00236 -0.0613 0.3896 0.3850 4.250 0.7208 0.00907 0.00246 -0.0601 0.3828 0.3889 4.500 0.7423 0.00919 0.00258 -0.0587 0.3772 0.3933 4.750 0.7655 0.00925 0.00268 -0.0577 0.3740 0.3971 5.000 0.7881 0.00932 0.00280 -0.0566 0.3701 0.4015 5.250 0.8086 0.00947 0.00293 -0.0551 0.3618 0.4061 5.500 0.8317 0.00954 0.00304 -0.0541 0.3580 0.4093 5.750 0.8525 0.00967 0.00318 -0.0526 0.3481 0.4148 6.000 0.8729 0.00982 0.00332 -0.0511 0.3343 0.4204 6.500 0.9069 0.01032 0.00369 -0.0469 0.2895 0.4330 6.750 0.9188 0.01076 0.00399 -0.0439 0.2563 0.4392 7.000 0.9249 0.01143 0.00444 -0.0398 0.2092 0.4466 7.250 0.9329 0.01204 0.00488 -0.0361 0.1720 0.4559 7.500 0.9422 0.01259 0.00532 -0.0328 0.1408 0.4709 7.750 0.9513 0.01312 0.00579 -0.0295 0.1117 0.4996 8.250 1.1069 0.01508 0.00833 -0.0549 0.0187 0.9953 8.500 1.1343 0.01560 0.00884 -0.0555 0.0158 0.9984 8.750 1.1671 0.01610 0.00935 -0.0572 0.0141 0.9999 9.000 1.1824 0.01654 0.00980 -0.0552 0.0131 1.0000 9.250 1.1953 0.01700 0.01028 -0.0527 0.0123 1.0000 9.500 1.2070 0.01753 0.01083 -0.0501 0.0115 1.0000 9.750 1.2208 0.01798 0.01132 -0.0479 0.0110 1.0000 10.000 1.2337 0.01849 0.01186 -0.0456 0.0105 1.0000 10.250 1.2460 0.01905 0.01245 -0.0433 0.0101 1.0000 10.500 1.2579 0.01966 0.01309 -0.0410 0.0097 1.0000 10.750 1.2690 0.02035 0.01380 -0.0388 0.0092 1.0000 11.000 1.2793 0.02111 0.01461 -0.0365 0.0090 1.0000 11.250 1.2878 0.02200 0.01554 -0.0341 0.0085 1.0000 11.500 1.2990 0.02278 0.01637 -0.0321 0.0083 1.0000 11.750 1.3089 0.02367 0.01730 -0.0301 0.0081 1.0000 12.000 1.3190 0.02457 0.01825 -0.0282 0.0078 1.0000 12.250 1.3276 0.02562 0.01935 -0.0263 0.0077 1.0000 12.500 1.3374 0.02662 0.02040 -0.0246 0.0074 1.0000 12.750 1.3457 0.02775 0.02158 -0.0229 0.0071 1.0000 13.000 1.3528 0.02902 0.02291 -0.0211 0.0071 1.0000 13.250 1.3606 0.03027 0.02419 -0.0196 0.0067 1.0000 13.500 1.3667 0.03171 0.02569 -0.0180 0.0066 1.0000 13.750 1.3716 0.03329 0.02732 -0.0165 0.0065 1.0000 14.000 1.3722 0.03530 0.02940 -0.0149 0.0062 1.0000 14.250 1.3787 0.03687 0.03103 -0.0137 0.0061 1.0000 14.500 1.3824 0.03875 0.03299 -0.0126 0.0061 1.0000 14.750 1.3881 0.04050 0.03480 -0.0117 0.0059 1.0000 15.000 1.3905 0.04263 0.03701 -0.0107 0.0058 1.0000 15.250 1.3908 0.04503 0.03950 -0.0099 0.0058 1.0000 15.500 1.3954 0.04706 0.04159 -0.0093 0.0057 1.0000 15.750 1.3965 0.04950 0.04411 -0.0087 0.0056 1.0000 16.000 1.3965 0.05212 0.04680 -0.0082 0.0055 1.0000 16.250 1.3959 0.05487 0.04963 -0.0079 0.0054 1.0000 16.500 1.3963 0.05758 0.05242 -0.0076 0.0053 1.0000 16.750 1.3940 0.06064 0.05556 -0.0076 0.0052 1.0000 17.000 1.3909 0.06388 0.05889 -0.0076 0.0052 1.0000 17.250 1.3888 0.06710 0.06218 -0.0077 0.0051 1.0000 17.500 1.3827 0.07091 0.06609 -0.0081 0.0051 1.0000 17.750 1.3834 0.07391 0.06915 -0.0085 0.0049 1.0000 18.000 1.3769 0.07794 0.07328 -0.0092 0.0049 1.0000 18.250 1.3721 0.08181 0.07722 -0.0100 0.0048 1.0000 18.500 1.3662 0.08591 0.08142 -0.0109 0.0048 1.0000 18.750 1.3617 0.08983 0.08542 -0.0119 0.0047 1.0000 19.000 1.3518 0.09459 0.09026 -0.0131 0.0046 1.0000 19.250 1.3446 0.09897 0.09473 -0.0144 0.0046 1.0000