UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 500,000 Max Cl/Cd: 60.13 at α=15.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ui1720-il-500000.txt Download as CSV file: xf-ui1720-il-500000.csv |
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 = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.7515 0.07645 0.07363 -0.0283 1.0004 0.0221
-12.750 -0.7994 0.06533 0.06241 -0.0365 1.0004 0.0220
-12.500 -0.8480 0.05541 0.05243 -0.0436 1.0004 0.0218
-12.250 -0.8945 0.03303 0.02949 -0.0724 1.0004 0.0214
-12.000 -0.8809 0.02932 0.02548 -0.0757 1.0004 0.0220
-11.750 -0.8643 0.02687 0.02293 -0.0771 1.0004 0.0227
-11.500 -0.8439 0.02524 0.02121 -0.0776 1.0004 0.0234
-11.250 -0.8224 0.02380 0.01965 -0.0779 1.0004 0.0243
-11.000 -0.8000 0.02243 0.01807 -0.0780 1.0004 0.0253
-10.750 -0.7776 0.02116 0.01680 -0.0781 1.0004 0.0265
-10.500 -0.7535 0.02025 0.01582 -0.0778 1.0004 0.0278
-10.250 -0.7295 0.01923 0.01468 -0.0776 1.0004 0.0293
-10.000 -0.7046 0.01854 0.01399 -0.0773 1.0004 0.0308
-9.750 -0.5696 0.01768 0.01230 -0.0997 0.7286 0.0360
-9.500 -0.5534 0.01820 0.01196 -0.0974 0.4876 0.0376
-9.250 -0.5283 0.01843 0.01182 -0.0967 0.3907 0.0395
-9.000 -0.5021 0.01830 0.01142 -0.0963 0.3474 0.0417
-8.750 -0.4747 0.01845 0.01148 -0.0959 0.3263 0.0434
-8.500 -0.4474 0.01828 0.01104 -0.0956 0.3137 0.0458
-8.250 -0.4200 0.01828 0.01107 -0.0952 0.3062 0.0473
-8.000 -0.3923 0.01833 0.01103 -0.0948 0.3001 0.0493
-7.750 -0.3653 0.01809 0.01057 -0.0945 0.2944 0.0514
-7.500 -0.3377 0.01809 0.01060 -0.0941 0.2913 0.0529
-7.250 -0.3099 0.01802 0.01045 -0.0938 0.2886 0.0549
-7.000 -0.2824 0.01773 0.00997 -0.0935 0.2860 0.0570
-6.750 -0.2551 0.01760 0.00987 -0.0931 0.2835 0.0585
-6.500 -0.2274 0.01760 0.00980 -0.0927 0.2812 0.0605
-6.250 -0.1997 0.01757 0.00958 -0.0923 0.2789 0.0625
-6.000 -0.1732 0.01714 0.00912 -0.0920 0.2765 0.0644
-5.750 -0.1456 0.01707 0.00903 -0.0916 0.2753 0.0661
-5.500 -0.1177 0.01691 0.00880 -0.0912 0.2744 0.0680
-5.250 -0.0895 0.01681 0.00856 -0.0909 0.2735 0.0696
-5.000 -0.0624 0.01617 0.00792 -0.0906 0.2725 0.0714
-4.750 -0.0346 0.01601 0.00775 -0.0902 0.2715 0.0731
-4.500 -0.0067 0.01584 0.00752 -0.0898 0.2705 0.0747
-4.250 0.0212 0.01566 0.00726 -0.0895 0.2695 0.0763
-4.000 0.0494 0.01556 0.00706 -0.0891 0.2684 0.0775
-3.750 0.0767 0.01502 0.00651 -0.0888 0.2673 0.0792
-3.500 0.1046 0.01484 0.00632 -0.0884 0.2664 0.0807
-3.250 0.1325 0.01470 0.00614 -0.0880 0.2655 0.0822
-3.000 0.1605 0.01460 0.00600 -0.0877 0.2648 0.0838
-2.750 0.1885 0.01452 0.00586 -0.0873 0.2640 0.0853
-2.500 0.2165 0.01446 0.00574 -0.0869 0.2632 0.0863
-2.250 0.2441 0.01421 0.00550 -0.0866 0.2625 0.0884
-2.000 0.2720 0.01420 0.00548 -0.0863 0.2618 0.0906
-1.750 0.3000 0.01425 0.00550 -0.0859 0.2610 0.0929
-1.500 0.3280 0.01436 0.00557 -0.0856 0.2603 0.0951
-1.250 0.3559 0.01443 0.00564 -0.0853 0.2596 0.0979
-1.000 0.3838 0.01462 0.00585 -0.0850 0.2590 0.1017
-0.750 0.4120 0.01467 0.00589 -0.0847 0.2588 0.1062
-0.500 0.4402 0.01465 0.00591 -0.0844 0.2586 0.1134
-0.250 0.4684 0.01467 0.00597 -0.0842 0.2584 0.1236
0.000 0.4966 0.01468 0.00606 -0.0839 0.2581 0.1426
0.250 0.5247 0.01469 0.00620 -0.0837 0.2579 0.1785
0.500 0.5527 0.01470 0.00637 -0.0835 0.2577 0.2291
0.750 0.5805 0.01473 0.00658 -0.0833 0.2575 0.2858
1.000 0.6083 0.01478 0.00680 -0.0831 0.2573 0.3494
1.250 0.6360 0.01483 0.00706 -0.0829 0.2571 0.4212
1.500 0.6634 0.01487 0.00733 -0.0826 0.2568 0.5039
1.750 0.6901 0.01486 0.00764 -0.0822 0.2566 0.6117
2.000 0.7138 0.01468 0.00795 -0.0810 0.2564 0.7714
2.250 0.7432 0.01458 0.00818 -0.0808 0.2562 0.9996
2.500 0.7710 0.01490 0.00847 -0.0805 0.2560 0.9996
2.750 0.7987 0.01524 0.00878 -0.0802 0.2558 0.9996
3.000 0.8263 0.01559 0.00911 -0.0799 0.2556 0.9996
3.250 0.8538 0.01591 0.00942 -0.0797 0.2552 0.9996
3.500 0.8812 0.01623 0.00973 -0.0794 0.2547 0.9996
3.750 0.9085 0.01660 0.01009 -0.0791 0.2544 0.9996
4.000 0.9356 0.01700 0.01050 -0.0787 0.2541 0.9996
4.250 0.9626 0.01742 0.01092 -0.0784 0.2539 0.9996
4.500 0.9894 0.01785 0.01137 -0.0781 0.2536 0.9996
4.750 1.0161 0.01830 0.01184 -0.0778 0.2534 0.9996
5.000 1.0426 0.01878 0.01234 -0.0774 0.2531 0.9996
5.250 1.0688 0.01927 0.01287 -0.0770 0.2528 0.9996
5.500 1.0949 0.01979 0.01342 -0.0767 0.2526 0.9996
5.750 1.1208 0.02033 0.01400 -0.0763 0.2523 0.9996
6.000 1.1464 0.02091 0.01462 -0.0759 0.2521 0.9996
6.250 1.1717 0.02151 0.01527 -0.0754 0.2518 0.9996
6.500 1.1968 0.02214 0.01597 -0.0750 0.2516 0.9996
6.750 1.2215 0.02281 0.01670 -0.0745 0.2514 0.9996
7.000 1.2463 0.02342 0.01736 -0.0741 0.2510 0.9996
7.250 1.2718 0.02386 0.01782 -0.0737 0.2503 0.9996
7.500 1.2977 0.02419 0.01816 -0.0733 0.2495 0.9996
7.750 1.3232 0.02460 0.01859 -0.0729 0.2488 0.9996
8.000 1.3474 0.02523 0.01928 -0.0724 0.2484 0.9996
8.250 1.3718 0.02578 0.01988 -0.0720 0.2479 0.9996
8.500 1.3960 0.02636 0.02050 -0.0715 0.2474 0.9996
8.750 1.4199 0.02696 0.02115 -0.0710 0.2470 0.9996
9.000 1.4441 0.02751 0.02173 -0.0705 0.2464 0.9996
9.250 1.4679 0.02811 0.02237 -0.0701 0.2458 0.9996
9.500 1.4906 0.02891 0.02322 -0.0695 0.2452 0.9996
9.750 1.5119 0.03000 0.02438 -0.0689 0.2446 0.9996
10.000 1.5283 0.03204 0.02653 -0.0681 0.2437 0.9996
10.250 1.5404 0.03418 0.02886 -0.0667 0.2429 0.9996
10.500 1.5605 0.03463 0.02944 -0.0658 0.2424 0.9996
10.750 1.5794 0.03520 0.03014 -0.0648 0.2416 0.9996
11.000 1.5963 0.03605 0.03113 -0.0637 0.2406 0.9996
11.250 1.6101 0.03728 0.03252 -0.0624 0.2395 0.9996
11.500 1.6219 0.03866 0.03405 -0.0610 0.2383 0.9996
11.750 1.6352 0.03979 0.03530 -0.0597 0.2371 0.9996
12.000 1.6542 0.04025 0.03583 -0.0588 0.2359 0.9996
12.250 1.6788 0.04013 0.03572 -0.0583 0.2348 0.9996
12.500 1.7055 0.03982 0.03541 -0.0579 0.2339 0.9996
12.750 1.7309 0.03973 0.03532 -0.0574 0.2331 0.9996
13.000 1.7528 0.03995 0.03556 -0.0567 0.2323 0.9996
13.250 1.7809 0.03957 0.03516 -0.0565 0.2315 0.9996
13.500 1.8158 0.03850 0.03401 -0.0567 0.2304 0.9996
13.750 1.8347 0.03971 0.03519 -0.0562 0.2283 0.9996
14.000 1.8482 0.03927 0.03490 -0.0543 0.2270 0.9996
14.250 1.8580 0.03955 0.03532 -0.0523 0.2252 0.9996
14.500 1.8715 0.03974 0.03560 -0.0506 0.2236 0.9996
14.750 1.8949 0.03906 0.03494 -0.0497 0.2219 0.9996
15.000 1.9308 0.03726 0.03308 -0.0497 0.2200 0.9996
15.250 1.9632 0.03578 0.03153 -0.0494 0.2185 0.9996
15.500 1.9986 0.03437 0.03003 -0.0496 0.2170 0.9996
15.750 2.0287 0.03374 0.02931 -0.0496 0.2152 0.9996
16.000 2.0272 0.03449 0.03023 -0.0462 0.2140 0.9996
16.250 2.0201 0.03564 0.03157 -0.0428 0.2125 0.9996
16.500 2.0157 0.03692 0.03303 -0.0404 0.2106 0.9996
16.750 2.0224 0.03758 0.03380 -0.0393 0.2083 0.9996
17.000 2.0438 0.03715 0.03339 -0.0389 0.2057 0.9996
17.250 2.0667 0.03671 0.03293 -0.0387 0.2034 0.9996
17.500 2.0665 0.03870 0.03507 -0.0384 0.2011 0.9996
17.750 2.0459 0.04335 0.04000 -0.0393 0.1979 0.9996
18.000 2.0223 0.04919 0.04605 -0.0419 0.1943 0.9996
18.250 2.0113 0.05398 0.05095 -0.0447 0.1907 0.9996
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