UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=200,000 Ncrit=5
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 200,000 Max Cl/Cd: 44.88 at α=5.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ui1720-il-200000-n5.txt Download as CSV file: xf-ui1720-il-200000-n5.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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.750 -0.5616 0.03194 0.02632 -0.0877 0.5612 0.0365
-9.500 -0.5377 0.03242 0.02648 -0.0870 0.4595 0.0374
-9.250 -0.5147 0.03173 0.02546 -0.0874 0.4067 0.0387
-8.750 -0.3962 0.06733 0.06163 -0.0413 0.3173 0.0369
-8.500 -0.4456 0.02706 0.01961 -0.0900 0.3399 0.0452
-8.250 -0.4198 0.02672 0.01911 -0.0899 0.3281 0.0467
-8.000 -0.3937 0.02642 0.01866 -0.0897 0.3190 0.0485
-7.500 -0.3420 0.02503 0.01680 -0.0898 0.3070 0.0527
-7.250 -0.3156 0.02442 0.01598 -0.0897 0.3024 0.0550
-7.000 -0.2895 0.02361 0.01487 -0.0897 0.2985 0.0572
-6.750 -0.2628 0.02347 0.01466 -0.0893 0.2949 0.0588
-6.500 -0.2361 0.02294 0.01391 -0.0891 0.2922 0.0610
-6.250 -0.2092 0.02222 0.01291 -0.0890 0.2898 0.0633
-6.000 -0.1822 0.02194 0.01262 -0.0887 0.2874 0.0648
-5.750 -0.1550 0.02159 0.01215 -0.0884 0.2851 0.0667
-5.500 -0.1277 0.02108 0.01138 -0.0882 0.2831 0.0689
-5.250 -0.1005 0.02061 0.01077 -0.0879 0.2813 0.0706
-5.000 -0.0733 0.02032 0.01043 -0.0876 0.2795 0.0721
-4.750 -0.0460 0.02004 0.01003 -0.0872 0.2780 0.0740
-4.500 -0.0186 0.01975 0.00956 -0.0869 0.2765 0.0759
-4.250 0.0091 0.01945 0.00906 -0.0865 0.2752 0.0775
-4.000 0.0365 0.01909 0.00872 -0.0862 0.2742 0.0790
-3.750 0.0642 0.01886 0.00845 -0.0859 0.2732 0.0807
-3.500 0.0920 0.01862 0.00817 -0.0856 0.2722 0.0823
-3.250 0.1198 0.01841 0.00788 -0.0852 0.2712 0.0842
-3.000 0.1477 0.01826 0.00762 -0.0849 0.2703 0.0861
-2.750 0.1754 0.01803 0.00741 -0.0846 0.2693 0.0879
-2.500 0.2032 0.01790 0.00726 -0.0842 0.2684 0.0898
-2.250 0.2310 0.01780 0.00712 -0.0839 0.2676 0.0920
-2.000 0.2590 0.01773 0.00699 -0.0836 0.2668 0.0948
-1.750 0.2869 0.01764 0.00689 -0.0833 0.2659 0.0977
-1.500 0.3148 0.01759 0.00683 -0.0830 0.2650 0.1012
-1.250 0.3427 0.01758 0.00677 -0.0827 0.2641 0.1052
-1.000 0.3706 0.01755 0.00674 -0.0824 0.2632 0.1098
-0.750 0.3986 0.01757 0.00674 -0.0822 0.2625 0.1166
-0.500 0.4265 0.01760 0.00678 -0.0819 0.2618 0.1255
-0.250 0.4544 0.01766 0.00686 -0.0817 0.2612 0.1378
0.000 0.4823 0.01774 0.00697 -0.0814 0.2606 0.1557
0.500 0.5378 0.01798 0.00736 -0.0810 0.2595 0.2186
0.750 0.5655 0.01813 0.00763 -0.0808 0.2589 0.2631
1.000 0.5930 0.01819 0.00785 -0.0806 0.2586 0.3171
1.250 0.6203 0.01824 0.00812 -0.0803 0.2582 0.3808
1.500 0.6473 0.01828 0.00841 -0.0800 0.2579 0.4586
1.750 0.6735 0.01826 0.00873 -0.0794 0.2575 0.5623
2.000 0.6963 0.01809 0.00904 -0.0780 0.2572 0.7190
2.500 0.7527 0.01828 0.00955 -0.0772 0.2564 0.9996
2.750 0.7801 0.01866 0.00989 -0.0769 0.2561 0.9996
3.000 0.8074 0.01905 0.01026 -0.0767 0.2557 0.9996
3.250 0.8345 0.01945 0.01064 -0.0764 0.2553 0.9996
3.500 0.8615 0.01988 0.01106 -0.0761 0.2550 0.9996
3.750 0.8883 0.02033 0.01150 -0.0757 0.2546 0.9996
4.000 0.9149 0.02079 0.01197 -0.0754 0.2542 0.9996
4.250 0.9414 0.02127 0.01246 -0.0751 0.2538 0.9996
4.500 0.9676 0.02178 0.01299 -0.0747 0.2535 0.9996
4.750 0.9937 0.02229 0.01352 -0.0743 0.2530 0.9996
5.000 1.0196 0.02278 0.01404 -0.0739 0.2524 0.9996
5.250 1.0453 0.02329 0.01458 -0.0735 0.2518 0.9996
5.500 1.0707 0.02386 0.01519 -0.0731 0.2513 0.9996
5.750 1.0959 0.02446 0.01583 -0.0727 0.2509 0.9996
6.000 1.1208 0.02509 0.01651 -0.0723 0.2505 0.9996
6.250 1.1454 0.02574 0.01722 -0.0718 0.2501 0.9996
6.500 1.1698 0.02642 0.01796 -0.0713 0.2497 0.9996
6.750 1.1938 0.02713 0.01874 -0.0708 0.2493 0.9996
7.000 1.2175 0.02786 0.01954 -0.0703 0.2489 0.9996
7.250 1.2408 0.02862 0.02037 -0.0698 0.2485 0.9996
7.500 1.2638 0.02942 0.02125 -0.0692 0.2481 0.9996
7.750 1.2865 0.03024 0.02215 -0.0686 0.2476 0.9996
8.000 1.3088 0.03108 0.02307 -0.0680 0.2472 0.9996
8.250 1.3314 0.03182 0.02387 -0.0675 0.2467 0.9996
8.500 1.3541 0.03252 0.02463 -0.0669 0.2460 0.9996
8.750 1.3769 0.03320 0.02535 -0.0663 0.2454 0.9996
9.000 1.3998 0.03388 0.02606 -0.0658 0.2448 0.9996
9.250 1.4229 0.03457 0.02678 -0.0653 0.2441 0.9996
9.500 1.4450 0.03552 0.02775 -0.0648 0.2433 0.9996
9.750 1.4601 0.03688 0.02930 -0.0637 0.2426 0.9996
10.000 1.4709 0.03857 0.03126 -0.0623 0.2419 0.9996
10.250 1.4764 0.04070 0.03367 -0.0606 0.2406 0.9996
10.500 1.4757 0.04329 0.03655 -0.0587 0.2389 0.9996
10.750 1.4689 0.04629 0.03982 -0.0567 0.2371 0.9996
11.000 1.4498 0.05006 0.04385 -0.0543 0.2354 0.9996
11.250 1.3902 0.05704 0.05110 -0.0523 0.2330 0.9996
11.500 1.3267 0.06815 0.06240 -0.0582 0.2298 0.9996
11.750 1.3395 0.06940 0.06367 -0.0579 0.2292 0.9996
12.000 1.3558 0.07011 0.06440 -0.0572 0.2287 0.9996
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