UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 100,000 Max Cl/Cd: 29.08 at α=4.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-ui1720-il-100000-n5.txt Download as CSV file: xf-ui1720-il-100000-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 = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.3179 0.11311 0.10638 -0.0120 0.3948 0.0446
-9.750 -0.3160 0.10885 0.10208 -0.0142 0.3873 0.0450
-9.500 -0.3139 0.10479 0.09801 -0.0165 0.3805 0.0461
-9.250 -0.3026 0.10257 0.09572 -0.0172 0.3706 0.0478
-9.000 -0.2995 0.09868 0.09182 -0.0194 0.3659 0.0491
-8.750 -0.3001 0.09388 0.08703 -0.0224 0.3627 0.0500
-8.500 -0.3022 0.08869 0.08187 -0.0259 0.3602 0.0512
-8.250 -0.2887 0.08706 0.08019 -0.0262 0.3535 0.0528
-8.000 -0.2859 0.08298 0.07609 -0.0291 0.3506 0.0545
-7.000 -0.2752 0.05036 0.04313 -0.0678 0.3463 0.0637
-6.500 -0.2371 0.03850 0.03022 -0.0798 0.3390 0.0709
-6.250 -0.2125 0.03759 0.02916 -0.0801 0.3342 0.0731
-6.000 -0.1881 0.03319 0.02379 -0.0834 0.3310 0.0776
-5.750 -0.1624 0.03262 0.02322 -0.0832 0.3271 0.0794
-5.500 -0.1362 0.03168 0.02211 -0.0833 0.3234 0.0819
-5.250 -0.1092 0.02986 0.01975 -0.0841 0.3203 0.0853
-5.000 -0.0825 0.02883 0.01846 -0.0842 0.3176 0.0876
-4.750 -0.0557 0.02821 0.01769 -0.0841 0.3152 0.0899
-4.500 -0.0284 0.02743 0.01662 -0.0841 0.3131 0.0924
-4.250 -0.0005 0.02661 0.01538 -0.0841 0.3113 0.0953
-4.000 0.0271 0.02591 0.01456 -0.0840 0.3095 0.0973
-3.750 0.0547 0.02544 0.01402 -0.0838 0.3077 0.0994
-3.500 0.0825 0.02501 0.01348 -0.0836 0.3060 0.1021
-3.250 0.1106 0.02457 0.01284 -0.0834 0.3044 0.1049
-3.000 0.1388 0.02416 0.01225 -0.0831 0.3029 0.1071
-2.750 0.1662 0.02384 0.01195 -0.0828 0.3014 0.1097
-2.500 0.1939 0.02363 0.01169 -0.0826 0.3001 0.1131
-2.250 0.2218 0.02344 0.01139 -0.0823 0.2989 0.1167
-2.000 0.2496 0.02325 0.01111 -0.0819 0.2978 0.1200
-1.750 0.2771 0.02312 0.01099 -0.0817 0.2967 0.1242
-1.500 0.3049 0.02309 0.01090 -0.0814 0.2957 0.1300
-1.250 0.3325 0.02306 0.01084 -0.0811 0.2949 0.1361
-1.000 0.3602 0.02312 0.01086 -0.0808 0.2939 0.1438
-0.750 0.3877 0.02317 0.01094 -0.0806 0.2930 0.1540
-0.500 0.4152 0.02320 0.01106 -0.0803 0.2920 0.1687
-0.250 0.4427 0.02325 0.01123 -0.0800 0.2910 0.1896
0.000 0.4700 0.02333 0.01145 -0.0798 0.2899 0.2216
0.250 0.4970 0.02342 0.01175 -0.0795 0.2890 0.2684
0.500 0.5241 0.02355 0.01211 -0.0793 0.2882 0.3320
0.750 0.5510 0.02369 0.01252 -0.0790 0.2874 0.4135
1.000 0.5769 0.02379 0.01299 -0.0785 0.2867 0.5194
1.250 0.5997 0.02375 0.01345 -0.0771 0.2860 0.6658
1.500 0.6252 0.02356 0.01376 -0.0757 0.2853 0.9996
1.750 0.6523 0.02413 0.01423 -0.0755 0.2846 0.9996
2.000 0.6791 0.02472 0.01475 -0.0753 0.2840 0.9996
2.250 0.7057 0.02535 0.01531 -0.0750 0.2834 0.9996
2.500 0.7320 0.02600 0.01592 -0.0747 0.2828 0.9996
2.750 0.7580 0.02668 0.01657 -0.0744 0.2822 0.9996
3.000 0.7837 0.02740 0.01726 -0.0741 0.2817 0.9996
3.250 0.8091 0.02815 0.01800 -0.0738 0.2812 0.9996
3.500 0.8343 0.02894 0.01879 -0.0734 0.2807 0.9996
3.750 0.8592 0.02973 0.01957 -0.0730 0.2800 0.9996
4.000 0.8841 0.03049 0.02033 -0.0726 0.2793 0.9996
4.250 0.9088 0.03127 0.02108 -0.0723 0.2786 0.9996
4.500 0.9333 0.03209 0.02188 -0.0719 0.2779 0.9996
4.750 0.9574 0.03299 0.02280 -0.0715 0.2773 0.9996
5.000 0.9808 0.03400 0.02383 -0.0710 0.2769 0.9996
5.250 1.0039 0.03508 0.02494 -0.0706 0.2764 0.9996
5.500 1.0264 0.03627 0.02616 -0.0702 0.2760 0.9996
5.750 1.0465 0.03769 0.02769 -0.0696 0.2755 0.9996
6.000 1.0635 0.03942 0.02962 -0.0690 0.2750 0.9996
6.250 1.0780 0.04145 0.03187 -0.0683 0.2743 0.9996
6.500 1.0873 0.04406 0.03477 -0.0675 0.2730 0.9996
6.750 1.0913 0.04729 0.03830 -0.0669 0.2714 0.9996
7.000 1.0878 0.05148 0.04278 -0.0665 0.2699 0.9996
7.250 1.0732 0.05674 0.04833 -0.0665 0.2672 0.9996
7.500 1.0547 0.06233 0.05412 -0.0672 0.2646 0.9996
7.750 1.0480 0.06609 0.05795 -0.0673 0.2626 0.9996
8.000 1.0537 0.06846 0.06035 -0.0671 0.2614 0.9996
8.250 1.0634 0.07046 0.06235 -0.0668 0.2604 0.9996
8.500 1.0757 0.07222 0.06412 -0.0663 0.2597 0.9996
8.750 1.0880 0.07404 0.06594 -0.0658 0.2590 0.9996
11.750 0.7458 0.13759 0.13067 -0.0735 0.2107 0.9996
12.000 0.7425 0.14014 0.13327 -0.0740 0.2080 0.9996
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Polar data table (+)
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