UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 200,000 Max Cl/Cd: 30.19 at α=2.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ui1720-il-200000.txt Download as CSV file: xf-ui1720-il-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.2740 0.10710 0.10136 -0.0157 0.3485 0.0654
-9.000 -0.2686 0.10398 0.09825 -0.0173 0.3460 0.0678
-8.750 -0.2888 0.09816 0.09252 -0.0261 0.3479 0.0700
-8.500 -0.2620 0.09681 0.09109 -0.0212 0.3418 0.0714
-8.250 -0.2510 0.09439 0.08865 -0.0215 0.3388 0.0738
-8.000 -0.2791 0.08753 0.08194 -0.0352 0.3417 0.0775
-7.750 -0.2544 0.08567 0.07998 -0.0296 0.3368 0.0785
-7.500 -0.2368 0.08416 0.07839 -0.0276 0.3335 0.0804
-7.000 -0.2334 0.07549 0.06973 -0.0383 0.3314 0.0875
-6.750 -0.2166 0.07428 0.06848 -0.0360 0.3292 0.0897
-6.500 -0.2250 0.03629 0.02908 -0.0846 0.3350 0.0778
-6.250 -0.1901 0.04916 0.04265 -0.0762 0.3295 0.0962
-6.000 -0.1739 0.03896 0.03212 -0.0810 0.3285 0.0839
-5.750 -0.1508 0.03108 0.02311 -0.0864 0.3273 0.0870
-5.500 -0.1248 0.03183 0.02419 -0.0853 0.3249 0.0896
-5.250 -0.0982 0.02997 0.02199 -0.0860 0.3229 0.0927
-5.000 -0.0703 0.02780 0.01915 -0.0869 0.3211 0.0956
-4.750 -0.0440 0.02633 0.01757 -0.0870 0.3193 0.0980
-4.500 -0.0169 0.02579 0.01698 -0.0868 0.3177 0.1004
-4.250 0.0110 0.02501 0.01596 -0.0868 0.3162 0.1030
-4.000 0.0393 0.02422 0.01484 -0.0868 0.3148 0.1053
-3.750 0.0678 0.02369 0.01397 -0.0867 0.3133 0.1073
-3.500 0.0952 0.02300 0.01321 -0.0866 0.3117 0.1092
-3.250 0.1231 0.02255 0.01273 -0.0864 0.3108 0.1116
-3.000 0.1513 0.02218 0.01229 -0.0861 0.3097 0.1140
-2.750 0.1797 0.02182 0.01183 -0.0858 0.3088 0.1161
-2.500 0.2081 0.02163 0.01150 -0.0855 0.3080 0.1184
-2.250 0.2361 0.02120 0.01106 -0.0853 0.3071 0.1211
-2.000 0.2639 0.02100 0.01089 -0.0850 0.3063 0.1239
-1.750 0.2920 0.02091 0.01080 -0.0847 0.3056 0.1272
-1.500 0.3201 0.02091 0.01076 -0.0843 0.3049 0.1313
-1.250 0.3478 0.02077 0.01067 -0.0840 0.3042 0.1360
-1.000 0.3755 0.02080 0.01077 -0.0837 0.3036 0.1419
-0.750 0.4033 0.02086 0.01085 -0.0834 0.3031 0.1491
-0.500 0.4309 0.02093 0.01102 -0.0831 0.3026 0.1601
-0.250 0.4585 0.02102 0.01123 -0.0829 0.3021 0.1775
0.000 0.4860 0.02109 0.01150 -0.0827 0.3017 0.2100
0.250 0.5132 0.02115 0.01187 -0.0825 0.3013 0.2795
0.500 0.5398 0.02124 0.01236 -0.0823 0.3010 0.3812
0.750 0.5656 0.02139 0.01292 -0.0818 0.3007 0.4950
1.000 0.5893 0.02148 0.01353 -0.0807 0.3005 0.6361
1.250 0.6140 0.02125 0.01401 -0.0792 0.3003 0.9996
1.500 0.6411 0.02188 0.01457 -0.0789 0.3000 0.9996
1.750 0.6681 0.02248 0.01511 -0.0787 0.2993 0.9996
2.000 0.6948 0.02311 0.01569 -0.0784 0.2988 0.9996
2.250 0.7209 0.02388 0.01645 -0.0781 0.2986 0.9996
2.500 0.7465 0.02473 0.01731 -0.0777 0.2985 0.9996
2.750 0.7716 0.02567 0.01828 -0.0773 0.2985 0.9996
3.000 0.7961 0.02672 0.01939 -0.0769 0.2985 0.9996
3.250 0.8197 0.02793 0.02068 -0.0765 0.2988 0.9996
3.500 0.8418 0.02940 0.02227 -0.0760 0.2992 0.9996
3.750 0.8618 0.03131 0.02436 -0.0756 0.3002 0.9996
4.000 0.8798 0.03364 0.02690 -0.0751 0.3015 0.9996
4.250 0.8990 0.03553 0.02890 -0.0747 0.3015 0.9996
4.500 0.9102 0.03921 0.03285 -0.0746 0.3043 0.9996
4.750 0.9223 0.04261 0.03643 -0.0745 0.3066 0.9996
5.000 0.9350 0.04574 0.03967 -0.0745 0.3080 0.9996
5.250 0.9506 0.04849 0.04247 -0.0743 0.3093 0.9996
5.500 0.9678 0.05106 0.04505 -0.0742 0.3102 0.9996
5.750 0.9982 0.05187 0.04576 -0.0739 0.3127 0.9996
6.000 0.8090 0.08252 0.07740 -0.0925 0.3158 0.9996
6.250 0.8304 0.08393 0.07876 -0.0913 0.3147 0.9996
6.500 0.8537 0.08530 0.08011 -0.0899 0.3139 0.9996
6.750 0.8788 0.08671 0.08149 -0.0882 0.3132 0.9996
7.000 0.9065 0.08809 0.08284 -0.0863 0.3127 0.9996
7.250 0.9375 0.08941 0.08414 -0.0838 0.3122 0.9996
7.500 0.9734 0.09089 0.08558 -0.0813 0.3118 0.9996
7.750 0.8086 0.10601 0.10084 -0.0969 0.2867 0.9996
8.000 0.8169 0.10827 0.10308 -0.0970 0.2826 0.9996
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Polar data table (+)
Polar graphs
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