XFOIL Version 6.96 Calculated polar for: UNIVERSITY OF ILLINOIS UI-1720 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 = 9.000 alpha CL CD CDp CM Top_Xtr Bot_Xtr ------ -------- --------- --------- -------- -------- -------- -14.000 -0.7449 0.09525 0.09301 -0.0155 1.0004 0.0157 -13.750 -0.7642 0.08794 0.08564 -0.0201 1.0004 0.0158 -13.500 -1.0263 0.03211 0.02896 -0.0757 1.0004 0.0137 -13.250 -1.0184 0.02718 0.02377 -0.0798 1.0004 0.0142 -13.000 -1.0010 0.02493 0.02138 -0.0808 1.0004 0.0146 -12.750 -0.9805 0.02338 0.01973 -0.0811 1.0004 0.0150 -12.500 -0.9586 0.02212 0.01837 -0.0812 1.0004 0.0155 -12.250 -0.9357 0.02105 0.01720 -0.0811 1.0004 0.0159 -12.000 -0.9126 0.01996 0.01600 -0.0809 1.0004 0.0164 -11.750 -0.8899 0.01868 0.01464 -0.0809 1.0004 0.0171 -11.500 -0.8657 0.01780 0.01371 -0.0806 1.0004 0.0178 -11.250 -0.8409 0.01708 0.01291 -0.0802 1.0004 0.0185 -11.000 -0.8158 0.01642 0.01217 -0.0797 1.0004 0.0192 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0.2558 0.0549 -6.000 -0.1673 0.01265 0.00536 -0.0941 0.2548 0.0562 -5.750 -0.1394 0.01241 0.00509 -0.0937 0.2538 0.0577 -5.500 -0.1112 0.01233 0.00502 -0.0934 0.2529 0.0591 -5.250 -0.0829 0.01229 0.00494 -0.0931 0.2520 0.0605 -5.000 -0.0546 0.01223 0.00483 -0.0927 0.2510 0.0617 -4.750 -0.0263 0.01220 0.00475 -0.0923 0.2502 0.0626 -4.500 0.0015 0.01191 0.00442 -0.0920 0.2493 0.0640 -4.250 0.0295 0.01177 0.00427 -0.0916 0.2483 0.0652 -4.000 0.0576 0.01170 0.00418 -0.0912 0.2471 0.0663 -3.750 0.0856 0.01167 0.00411 -0.0909 0.2460 0.0676 -3.500 0.1135 0.01165 0.00406 -0.0904 0.2449 0.0687 -3.250 0.1414 0.01166 0.00403 -0.0900 0.2439 0.0694 -3.000 0.1691 0.01159 0.00394 -0.0896 0.2431 0.0705 -2.750 0.1973 0.01144 0.00379 -0.0893 0.2429 0.0720 -2.500 0.2256 0.01137 0.00371 -0.0890 0.2427 0.0733 -2.250 0.2539 0.01132 0.00365 -0.0886 0.2425 0.0746 -2.000 0.2822 0.01129 0.00360 -0.0883 0.2422 0.0759 -1.750 0.3106 0.01129 0.00358 -0.0880 0.2420 0.0773 -1.500 0.3388 0.01122 0.00351 -0.0877 0.2417 0.0795 -1.250 0.3671 0.01120 0.00349 -0.0873 0.2414 0.0819 -1.000 0.3954 0.01121 0.00350 -0.0870 0.2411 0.0844 -0.750 0.4236 0.01122 0.00350 -0.0867 0.2409 0.0874 -0.500 0.4518 0.01122 0.00352 -0.0864 0.2406 0.0927 -0.250 0.4801 0.01123 0.00356 -0.0861 0.2403 0.1000 0.000 0.5082 0.01124 0.00361 -0.0858 0.2400 0.1123 0.250 0.5363 0.01124 0.00367 -0.0855 0.2397 0.1318 0.500 0.5644 0.01124 0.00376 -0.0852 0.2395 0.1610 0.750 0.5924 0.01124 0.00386 -0.0850 0.2392 0.1962 1.000 0.6204 0.01125 0.00397 -0.0847 0.2389 0.2349 1.500 0.6762 0.01127 0.00424 -0.0842 0.2385 0.3288 1.750 0.7041 0.01128 0.00440 -0.0840 0.2382 0.3897 2.000 0.7318 0.01129 0.00457 -0.0837 0.2380 0.4555 2.250 0.7594 0.01128 0.00475 -0.0834 0.2378 0.5321 2.500 0.7866 0.01124 0.00495 -0.0831 0.2376 0.6276 2.750 0.8121 0.01107 0.00517 -0.0823 0.2374 0.7721 3.000 0.8401 0.01083 0.00533 -0.0819 0.2372 0.9996 3.250 0.8680 0.01103 0.00550 -0.0816 0.2370 0.9996 3.500 0.8958 0.01123 0.00569 -0.0813 0.2368 0.9996 3.750 0.9236 0.01144 0.00588 -0.0811 0.2366 0.9996 4.000 0.9512 0.01166 0.00609 -0.0808 0.2365 0.9996 4.250 0.9789 0.01188 0.00630 -0.0805 0.2363 0.9996 4.500 1.0064 0.01211 0.00652 -0.0802 0.2361 0.9996 4.750 1.0340 0.01235 0.00675 -0.0799 0.2359 0.9996 5.000 1.0614 0.01256 0.00696 -0.0796 0.2356 0.9996 5.250 1.0889 0.01277 0.00716 -0.0793 0.2352 0.9996 5.500 1.1162 0.01300 0.00739 -0.0790 0.2350 0.9996 5.750 1.1434 0.01326 0.00765 -0.0787 0.2348 0.9996 6.000 1.1705 0.01351 0.00792 -0.0784 0.2345 0.9996 6.250 1.1976 0.01378 0.00819 -0.0781 0.2343 0.9996 6.500 1.2245 0.01406 0.00848 -0.0778 0.2341 0.9996 6.750 1.2514 0.01433 0.00877 -0.0775 0.2339 0.9996 7.000 1.2782 0.01462 0.00907 -0.0772 0.2337 0.9996 7.250 1.3050 0.01488 0.00934 -0.0769 0.2333 0.9996 7.500 1.3317 0.01511 0.00958 -0.0766 0.2329 0.9996 7.750 1.3583 0.01536 0.00984 -0.0763 0.2325 0.9996 8.000 1.3848 0.01566 0.01015 -0.0760 0.2321 0.9996 8.250 1.4110 0.01600 0.01052 -0.0757 0.2319 0.9996 8.500 1.4371 0.01636 0.01090 -0.0753 0.2316 0.9996 8.750 1.4630 0.01673 0.01130 -0.0750 0.2312 0.9996 9.000 1.4887 0.01715 0.01174 -0.0746 0.2307 0.9996 9.250 1.5139 0.01768 0.01231 -0.0743 0.2302 0.9996 9.500 1.5380 0.01846 0.01314 -0.0738 0.2295 0.9996 9.750 1.5586 0.01992 0.01472 -0.0731 0.2284 0.9996 10.000 1.5841 0.02016 0.01500 -0.0727 0.2283 0.9996 10.250 1.6095 0.02038 0.01527 -0.0723 0.2281 0.9996 10.500 1.6353 0.02045 0.01538 -0.0719 0.2278 0.9996 10.750 1.6610 0.02049 0.01546 -0.0715 0.2274 0.9996 11.000 1.6862 0.02063 0.01565 -0.0711 0.2270 0.9996 11.250 1.7110 0.02084 0.01591 -0.0706 0.2266 0.9996 11.500 1.7358 0.02102 0.01614 -0.0702 0.2261 0.9996 11.750 1.7607 0.02110 0.01626 -0.0697 0.2254 0.9996 12.000 1.7859 0.02103 0.01623 -0.0692 0.2244 0.9996 12.250 1.8104 0.02104 0.01630 -0.0687 0.2234 0.9996 12.500 1.8347 0.02116 0.01647 -0.0682 0.2226 0.9996 12.750 1.8600 0.02100 0.01632 -0.0677 0.2214 0.9996 13.000 1.8866 0.02053 0.01583 -0.0673 0.2199 0.9996 13.250 1.9128 0.02020 0.01547 -0.0670 0.2185 0.9996 13.500 1.9374 0.02013 0.01538 -0.0665 0.2168 0.9996 13.750 1.9580 0.02075 0.01605 -0.0657 0.2147 0.9996 14.000 1.9822 0.02046 0.01583 -0.0650 0.2139 0.9996 14.250 2.0060 0.02030 0.01575 -0.0644 0.2127 0.9996 14.500 2.0300 0.02014 0.01565 -0.0638 0.2111 0.9996 14.750 2.0542 0.01998 0.01554 -0.0632 0.2091 0.9996 15.000 2.0782 0.01987 0.01547 -0.0627 0.2073 0.9996 15.250 2.1020 0.01978 0.01541 -0.0621 0.2054 0.9996 15.500 2.1236 0.01983 0.01545 -0.0613 0.2028 0.9996 15.750 2.1471 0.01987 0.01560 -0.0608 0.2001 0.9996 16.000 2.1712 0.01988 0.01569 -0.0603 0.1950 0.9996 16.250 2.1945 0.01985 0.01564 -0.0598 0.1847 0.9996 16.500 2.1981 0.02096 0.01655 -0.0569 0.1619 0.9996 16.750 2.1906 0.02270 0.01826 -0.0527 0.1504 0.9996 17.000 2.1827 0.02451 0.02011 -0.0490 0.1415 0.9996 17.250 2.1688 0.02692 0.02256 -0.0455 0.1331 0.9996 17.500 2.1480 0.03034 0.02605 -0.0431 0.1255 0.9996 17.750 2.1222 0.03520 0.03104 -0.0429 0.1190 0.9996 18.000 2.0843 0.04310 0.03914 -0.0460 0.1167 0.9996 18.250 2.0297 0.05449 0.05083 -0.0513 0.1187 0.9996 18.500 1.9457 0.06921 0.06593 -0.0566 0.1265 0.9996 18.750 1.8535 0.08442 0.08146 -0.0616 0.1328 0.9996