XFOIL Version 6.96 Calculated polar for: USA 34 AIRFOIL 1 1 Reynolds number fixed Mach number fixed xtrf = 1.000 (top) 1.000 (bottom) Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -16.500 -0.4562 0.08731 0.08404 -0.1171 0.9826 0.0335 -16.250 -0.4768 0.07919 0.07577 -0.1238 0.9788 0.0337 -16.000 -0.4788 0.07442 0.07095 -0.1280 0.9736 0.0339 -15.750 -0.4665 0.07131 0.06784 -0.1317 0.9703 0.0344 -15.500 -0.4701 0.06723 0.06373 -0.1346 0.9604 0.0346 -15.250 -0.4773 0.06265 0.05909 -0.1381 0.9483 0.0350 -15.000 -0.4834 0.05730 0.05366 -0.1435 0.9381 0.0352 -14.750 -0.4841 0.05144 0.04768 -0.1512 0.9288 0.0354 -14.500 -0.4822 0.04413 0.04021 -0.1628 0.9188 0.0358 -14.250 -0.4815 0.03266 0.02839 -0.1844 0.9017 0.0360 -14.000 -0.4513 0.02654 0.02186 -0.1987 0.8874 0.0365 -13.750 -0.4279 0.02442 0.01948 -0.2027 0.8737 0.0372 -13.500 -0.4166 0.02320 0.01805 -0.2023 0.8606 0.0376 -13.250 -0.4170 0.02208 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0.00435 -0.0928 0.5402 0.1870 1.250 0.6614 0.01203 0.00445 -0.0910 0.5343 0.1965 1.500 0.6821 0.01211 0.00458 -0.0896 0.5295 0.2110 1.750 0.7024 0.01218 0.00473 -0.0881 0.5251 0.2310 2.000 0.7228 0.01229 0.00489 -0.0867 0.5205 0.2559 2.250 0.7439 0.01243 0.00505 -0.0855 0.5161 0.2810 2.500 0.7665 0.01258 0.00522 -0.0845 0.5116 0.3026 2.750 0.7860 0.01268 0.00539 -0.0830 0.5079 0.3204 3.000 0.8058 0.01281 0.00556 -0.0815 0.5035 0.3384 3.250 0.8268 0.01296 0.00573 -0.0803 0.4990 0.3581 3.500 0.8526 0.01311 0.00590 -0.0801 0.4943 0.3845 3.750 0.8708 0.01318 0.00614 -0.0785 0.4905 0.4236 4.000 1.1246 0.01299 0.00720 -0.1280 0.4820 1.0000 4.250 1.1441 0.01323 0.00739 -0.1265 0.4784 1.0000 4.500 1.1659 0.01349 0.00759 -0.1255 0.4745 1.0000 4.750 1.1819 0.01369 0.00782 -0.1234 0.4713 1.0000 5.000 1.1960 0.01393 0.00806 -0.1210 0.4664 1.0000 5.250 1.2137 0.01418 0.00829 -0.1192 0.4628 1.0000 5.500 1.2317 0.01448 0.00853 -0.1176 0.4585 1.0000 5.750 1.2489 0.01476 0.00881 -0.1159 0.4545 1.0000 6.000 1.2659 0.01503 0.00911 -0.1141 0.4513 1.0000 6.250 1.2817 0.01532 0.00942 -0.1122 0.4472 1.0000 6.500 1.2979 0.01565 0.00973 -0.1104 0.4432 1.0000 6.750 1.3154 0.01602 0.01004 -0.1088 0.4389 1.0000 7.000 1.3321 0.01636 0.01041 -0.1072 0.4357 1.0000 7.250 1.3476 0.01672 0.01081 -0.1054 0.4319 1.0000 7.500 1.3638 0.01710 0.01121 -0.1037 0.4281 1.0000 7.750 1.3791 0.01753 0.01162 -0.1020 0.4242 1.0000 8.000 1.3956 0.01798 0.01202 -0.1005 0.4198 1.0000 8.250 1.4095 0.01845 0.01257 -0.0987 0.4159 1.0000 8.500 1.4233 0.01896 0.01312 -0.0969 0.4110 1.0000 8.750 1.4369 0.01953 0.01367 -0.0951 0.4064 1.0000 9.000 1.4513 0.02010 0.01420 -0.0935 0.4022 1.0000 9.250 1.4663 0.02064 0.01482 -0.0920 0.3984 1.0000 9.500 1.4804 0.02124 0.01546 -0.0905 0.3939 1.0000 9.750 1.4937 0.02190 0.01612 -0.0889 0.3893 1.0000 10.000 1.5047 0.02270 0.01689 -0.0871 0.3843 1.0000 10.250 1.5195 0.02333 0.01760 -0.0858 0.3801 1.0000 10.500 1.5321 0.02409 0.01840 -0.0843 0.3750 1.0000 10.750 1.5427 0.02497 0.01926 -0.0826 0.3699 1.0000 11.000 1.5539 0.02586 0.02018 -0.0811 0.3646 1.0000 11.250 1.5655 0.02675 0.02112 -0.0796 0.3588 1.0000 11.500 1.5745 0.02781 0.02217 -0.0779 0.3530 1.0000 11.750 1.5843 0.02885 0.02324 -0.0764 0.3474 1.0000 12.000 1.5943 0.02991 0.02434 -0.0750 0.3408 1.0000 12.250 1.5987 0.03134 0.02574 -0.0731 0.3338 1.0000 12.500 1.6081 0.03251 0.02696 -0.0717 0.3260 1.0000 12.750 1.6116 0.03409 0.02853 -0.0699 0.3183 1.0000 13.000 1.6189 0.03545 0.02993 -0.0685 0.3102 1.0000 13.250 1.6183 0.03741 0.03186 -0.0665 0.3008 1.0000 13.500 1.6228 0.03905 0.03354 -0.0650 0.2910 1.0000 13.750 1.6216 0.04117 0.03564 -0.0631 0.2804 1.0000 14.000 1.6153 0.04378 0.03821 -0.0611 0.2682 1.0000 14.250 1.6106 0.04633 0.04074 -0.0592 0.2552 1.0000 14.500 1.6040 0.04910 0.04350 -0.0575 0.2421 1.0000 14.750 1.5958 0.05214 0.04651 -0.0557 0.2307 1.0000 15.000 1.5848 0.05550 0.04984 -0.0541 0.2199 1.0000 15.250 1.5777 0.05857 0.05292 -0.0527 0.2108 1.0000 15.500 1.5715 0.06163 0.05598 -0.0515 0.2033 1.0000 15.750 1.5662 0.06467 0.05904 -0.0505 0.1971 1.0000 16.000 1.5592 0.06793 0.06230 -0.0495 0.1920 1.0000 16.250 1.5581 0.07058 0.06500 -0.0488 0.1871 1.0000 16.500 1.5551 0.07348 0.06794 -0.0482 0.1831 1.0000 16.750 1.5493 0.07671 0.07118 -0.0475 0.1791 1.0000 17.000 1.5509 0.07916 0.07368 -0.0471 0.1758 1.0000 17.250 1.5506 0.08182 0.07640 -0.0467 0.1723 1.0000 17.500 1.5487 0.08467 0.07928 -0.0463 0.1688 1.0000 17.750 1.5438 0.08787 0.08248 -0.0459 0.1650 1.0000 18.000 1.5454 0.09036 0.08505 -0.0457 0.1617 1.0000 18.250 1.5467 0.09290 0.08765 -0.0455 0.1582 1.0000 18.500 1.5417 0.09622 0.09099 -0.0454 0.1539 1.0000 18.750 1.5387 0.09924 0.09402 -0.0453 0.1498 1.0000 19.000 1.5396 0.10192 0.09679 -0.0454 0.1459 1.0000 19.250 1.5365 0.10506 0.09996 -0.0455 0.1410 1.0000