XFOIL Version 6.96 Calculated polar for: USA 22 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 ------ -------- --------- --------- -------- -------- -------- -11.000 -0.4234 0.12509 0.12348 -0.0006 1.0000 0.0033 -10.750 -0.4196 0.12098 0.11939 -0.0021 1.0000 0.0033 -9.250 -0.5851 0.02359 0.02092 -0.0765 0.9866 0.0036 -9.000 -0.5559 0.02079 0.01781 -0.0791 0.9763 0.0037 -8.750 -0.5260 0.01887 0.01564 -0.0809 0.9619 0.0038 -8.500 -0.4972 0.01738 0.01391 -0.0820 0.9445 0.0040 -8.250 -0.4709 0.01628 0.01258 -0.0821 0.9265 0.0041 -8.000 -0.4457 0.01538 0.01146 -0.0819 0.9103 0.0043 -7.750 -0.4204 0.01461 0.01049 -0.0816 0.8954 0.0045 -7.500 -0.3948 0.01394 0.00964 -0.0813 0.8797 0.0047 -7.250 -0.3689 0.01333 0.00885 -0.0809 0.8629 0.0048 -7.000 -0.3435 0.01242 0.00769 -0.0806 0.8444 0.0050 -6.750 -0.3177 0.01183 0.00690 -0.0802 0.8219 0.0053 -6.500 -0.2917 0.01144 0.00633 -0.0798 0.7916 0.0056 -6.250 -0.2656 0.01112 0.00581 -0.0794 0.7599 0.0059 -6.000 -0.2391 0.01082 0.00533 -0.0791 0.7344 0.0063 -5.750 -0.2121 0.01051 0.00488 -0.0788 0.7154 0.0067 -5.500 -0.1848 0.01025 0.00448 -0.0786 0.6986 0.0070 -5.250 -0.1575 0.00994 0.00403 -0.0784 0.6822 0.0075 -5.000 -0.1302 0.00965 0.00363 -0.0782 0.6657 0.0086 -4.750 -0.1027 0.00944 0.00333 -0.0780 0.6501 0.0096 -4.500 -0.0750 0.00927 0.00305 -0.0779 0.6355 0.0104 -4.250 -0.0473 0.00906 0.00274 -0.0777 0.6199 0.0123 -4.000 -0.0198 0.00890 0.00252 -0.0775 0.6031 0.0149 -3.750 0.0079 0.00877 0.00234 -0.0774 0.5857 0.0207 -3.500 0.0356 0.00869 0.00219 -0.0773 0.5690 0.0247 -3.250 0.0634 0.00863 0.00208 -0.0772 0.5517 0.0292 -3.000 0.0912 0.00861 0.00198 -0.0770 0.5337 0.0323 -2.750 0.1190 0.00862 0.00190 -0.0769 0.5165 0.0336 -2.500 0.1467 0.00854 0.00176 -0.0768 0.5011 0.0374 -2.250 0.1745 0.00852 0.00168 -0.0767 0.4864 0.0405 -2.000 0.2024 0.00851 0.00160 -0.0766 0.4735 0.0427 -1.750 0.2304 0.00849 0.00151 -0.0765 0.4625 0.0438 -1.500 0.2583 0.00846 0.00142 -0.0764 0.4522 0.0460 -1.250 0.2862 0.00842 0.00133 -0.0763 0.4426 0.0505 -1.000 0.3142 0.00840 0.00128 -0.0762 0.4341 0.0547 -0.750 0.3421 0.00841 0.00123 -0.0762 0.4250 0.0586 -0.500 0.3699 0.00837 0.00119 -0.0761 0.4144 0.0722 -0.250 0.3973 0.00820 0.00117 -0.0761 0.4044 0.1391 0.000 0.4250 0.00820 0.00117 -0.0760 0.3958 0.1598 0.250 0.4530 0.00815 0.00117 -0.0760 0.3900 0.1841 0.500 0.4807 0.00812 0.00121 -0.0759 0.3832 0.2231 0.750 0.5088 0.00813 0.00124 -0.0759 0.3775 0.2442 1.000 0.5367 0.00814 0.00128 -0.0759 0.3718 0.2631 1.250 0.5646 0.00819 0.00133 -0.0758 0.3665 0.2774 1.750 0.6206 0.00826 0.00142 -0.0758 0.3555 0.3027 2.000 0.6484 0.00831 0.00148 -0.0758 0.3500 0.3123 2.250 0.6763 0.00837 0.00154 -0.0757 0.3430 0.3190 2.500 0.7040 0.00844 0.00160 -0.0757 0.3357 0.3278 2.750 0.7317 0.00851 0.00168 -0.0757 0.3275 0.3389 3.000 0.7593 0.00856 0.00176 -0.0756 0.3204 0.3584 3.250 0.7868 0.00861 0.00185 -0.0756 0.3121 0.3869 3.500 0.8090 0.00771 0.00204 -0.0748 0.3047 0.8347 4.000 0.8682 0.00773 0.00226 -0.0755 0.2851 1.0000 4.250 0.8948 0.00795 0.00241 -0.0753 0.2696 1.0000 4.500 0.9208 0.00825 0.00260 -0.0751 0.2473 1.0000 4.750 0.9471 0.00851 0.00278 -0.0749 0.2315 1.0000 5.000 0.9728 0.00885 0.00300 -0.0746 0.2115 1.0000 5.250 0.9983 0.00920 0.00325 -0.0743 0.1914 1.0000 5.500 1.0238 0.00955 0.00351 -0.0740 0.1727 1.0000 5.750 1.0489 0.00996 0.00380 -0.0737 0.1522 1.0000 6.000 1.0682 0.01114 0.00454 -0.0727 0.0788 1.0000 6.250 1.0880 0.01228 0.00541 -0.0717 0.0158 1.0000 6.500 1.1132 0.01262 0.00576 -0.0713 0.0113 1.0000 6.750 1.1387 0.01292 0.00609 -0.0710 0.0100 1.0000 7.000 1.1638 0.01325 0.00645 -0.0707 0.0088 1.0000 7.250 1.1882 0.01367 0.00690 -0.0702 0.0075 1.0000 7.500 1.2127 0.01407 0.00733 -0.0698 0.0067 1.0000 7.750 1.2371 0.01444 0.00773 -0.0694 0.0060 1.0000 8.000 1.2610 0.01486 0.00817 -0.0689 0.0055 1.0000 8.250 1.2840 0.01538 0.00872 -0.0683 0.0049 1.0000 8.500 1.3066 0.01592 0.00932 -0.0677 0.0046 1.0000 8.750 1.3293 0.01643 0.00988 -0.0671 0.0043 1.0000 9.000 1.3515 0.01696 0.01048 -0.0664 0.0040 1.0000 9.250 1.3733 0.01749 0.01105 -0.0657 0.0037 1.0000 9.500 1.3948 0.01803 0.01162 -0.0650 0.0035 1.0000 9.750 1.4147 0.01870 0.01234 -0.0641 0.0032 1.0000 10.000 1.4320 0.01959 0.01332 -0.0628 0.0030 1.0000 10.250 1.4504 0.02032 0.01411 -0.0617 0.0029 1.0000 10.500 1.4672 0.02112 0.01500 -0.0604 0.0028 1.0000 10.750 1.4824 0.02200 0.01596 -0.0589 0.0027 1.0000 11.000 1.4957 0.02292 0.01697 -0.0572 0.0026 1.0000 11.250 1.5046 0.02392 0.01807 -0.0549 0.0025 1.0000 11.500 1.5117 0.02503 0.01928 -0.0525 0.0024 1.0000 11.750 1.5180 0.02627 0.02060 -0.0504 0.0023 1.0000 12.000 1.5229 0.02774 0.02216 -0.0486 0.0023 1.0000 12.250 1.5270 0.02942 0.02393 -0.0471 0.0022 1.0000 12.500 1.5294 0.03143 0.02605 -0.0459 0.0022 1.0000 12.750 1.5315 0.03369 0.02840 -0.0452 0.0021 1.0000 13.000 1.5322 0.03635 0.03116 -0.0450 0.0021 1.0000 13.250 1.5296 0.03962 0.03455 -0.0453 0.0020 1.0000 13.500 1.5263 0.04321 0.03825 -0.0459 0.0020 1.0000 13.750 1.5190 0.04745 0.04261 -0.0468 0.0020 1.0000 14.000 1.5094 0.05215 0.04744 -0.0480 0.0019 1.0000 14.250 1.4962 0.05743 0.05285 -0.0494 0.0019 1.0000 14.500 1.4829 0.06277 0.05832 -0.0508 0.0019 1.0000 14.750 1.4677 0.06841 0.06408 -0.0523 0.0019 1.0000 15.000 1.4515 0.07426 0.07005 -0.0540 0.0018 1.0000 15.250 1.4338 0.08044 0.07635 -0.0557 0.0018 1.0000 15.500 1.4212 0.08594 0.08195 -0.0573 0.0018 1.0000