UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Xfoil prediction polar at RE=50,000 Ncrit=9
| Details | Polar file |
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Airfoil: UNIVERSITY OF ILLINOIS UI-1720 AIRFOIL (ui1720-il) Reynolds number: 50,000 Max Cl/Cd: 10.11 at α=0.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ui1720-il-50000.txt Download as CSV file: xf-ui1720-il-50000.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 = 0.050 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3195 0.13346 0.12742 0.0050 1.0004 0.1727
-10.000 -0.3206 0.13202 0.12609 0.0034 1.0004 0.1790
-9.750 -0.3433 0.13439 0.12860 -0.0004 1.0004 0.1812
-9.500 -0.3004 0.12424 0.11863 0.0024 1.0004 0.1883
-9.250 -0.2983 0.12242 0.11701 0.0011 1.0004 0.1965
-9.000 -0.3240 0.12490 0.11968 -0.0028 1.0004 0.1994
-8.750 -0.2562 0.11472 0.10863 -0.0054 0.6407 0.2116
-8.500 -0.2755 0.11646 0.11031 -0.0096 0.6260 0.2179
-8.250 -0.2378 0.10932 0.10264 -0.0071 0.5789 0.2269
-8.000 -0.2472 0.10953 0.10282 -0.0101 0.5709 0.2366
-7.750 -0.2219 0.10400 0.09711 -0.0094 0.5527 0.2435
-7.500 -0.2224 0.10311 0.09621 -0.0115 0.5453 0.2557
-7.250 -0.2001 0.09840 0.09142 -0.0111 0.5338 0.2647
-7.000 -0.2136 0.09907 0.09216 -0.0145 0.5311 0.2767
-6.750 -0.1771 0.09297 0.08597 -0.0127 0.5201 0.2881
-6.500 -0.1776 0.09122 0.08428 -0.0146 0.5160 0.3002
-6.250 -0.1757 0.09039 0.08345 -0.0161 0.5119 0.3165
-6.000 -0.1441 0.08541 0.07842 -0.0146 0.5046 0.3299
-5.750 -0.1340 0.08296 0.07604 -0.0148 0.4999 0.3453
-5.500 -0.1255 0.08083 0.07393 -0.0153 0.4958 0.3627
-5.250 -0.1157 0.07875 0.07184 -0.0156 0.4920 0.3813
-5.000 -0.1011 0.07643 0.06947 -0.0149 0.4883 0.4022
-4.750 -0.0845 0.07403 0.06716 -0.0140 0.4845 0.4246
-4.500 -0.0691 0.07190 0.06507 -0.0133 0.4812 0.4485
-4.250 -0.0610 0.07042 0.06365 -0.0128 0.4790 0.4796
-4.000 -0.0383 0.06783 0.06106 -0.0106 0.4763 0.5075
-3.750 -0.0244 0.06596 0.05922 -0.0088 0.4743 0.5419
-3.500 0.0577 0.05101 0.04298 -0.0717 0.4736 0.2591
-3.250 0.0878 0.04848 0.04022 -0.0745 0.4715 0.2520
-3.000 0.1198 0.04604 0.03743 -0.0780 0.4697 0.2473
-2.750 0.1533 0.04385 0.03484 -0.0816 0.4683 0.2437
-2.500 0.1829 0.04275 0.03357 -0.0833 0.4673 0.2464
-2.250 0.2130 0.04184 0.03244 -0.0850 0.4664 0.2487
-2.000 0.2429 0.04122 0.03157 -0.0864 0.4658 0.2523
-1.750 0.2722 0.04089 0.03099 -0.0876 0.4652 0.2586
-1.500 0.2979 0.04090 0.03109 -0.0880 0.4646 0.2656
-1.250 0.3255 0.04109 0.03113 -0.0888 0.4639 0.2745
-1.000 0.3506 0.04147 0.03157 -0.0893 0.4635 0.2860
-0.750 0.3764 0.04205 0.03211 -0.0900 0.4637 0.3002
-0.500 0.4010 0.04285 0.03295 -0.0905 0.4648 0.3194
-0.250 0.4255 0.04376 0.03398 -0.0909 0.4664 0.3451
0.000 0.4505 0.04470 0.03504 -0.0913 0.4680 0.3855
0.250 0.4655 0.04781 0.03874 -0.0956 0.4786 0.4258
0.500 0.4841 0.04940 0.04091 -0.0966 0.4850 0.5229
0.750 0.4940 0.04886 0.04174 -0.0921 0.4882 0.9996
1.000 0.2637 0.07308 0.06462 -0.1240 0.8133 0.2944
1.250 0.2932 0.07452 0.06595 -0.1249 0.7940 0.3143
1.500 0.3193 0.07587 0.06731 -0.1252 0.7752 0.3422
1.750 0.3433 0.07714 0.06871 -0.1252 0.7570 0.3860
2.000 0.3900 0.07875 0.07173 -0.1279 0.7507 0.6305
2.250 0.4033 0.07912 0.07215 -0.1248 0.7317 0.9996
2.500 0.4207 0.08080 0.07346 -0.1239 0.7125 0.9996
2.750 0.4336 0.08235 0.07474 -0.1225 0.6939 0.9996
3.000 0.4434 0.08398 0.07615 -0.1211 0.6768 0.9996
3.250 0.4571 0.08613 0.07809 -0.1204 0.6633 0.9996
3.500 0.4907 0.08919 0.08090 -0.1216 0.6529 0.9996
3.750 0.4934 0.09053 0.08211 -0.1197 0.6365 0.9996
4.000 0.5312 0.09470 0.08606 -0.1214 0.6298 0.9996
4.250 0.5340 0.09557 0.08683 -0.1194 0.6132 0.9996
4.500 0.5337 0.09712 0.08827 -0.1177 0.5996 0.9996
4.750 0.5672 0.10058 0.09158 -0.1187 0.5921 0.9996
5.000 0.5613 0.10173 0.09266 -0.1168 0.5781 0.9996
5.250 0.5980 0.10563 0.09642 -0.1179 0.5714 0.9996
5.500 0.5871 0.10643 0.09715 -0.1158 0.5574 0.9996
5.750 0.6224 0.11039 0.10100 -0.1167 0.5513 0.9996
6.000 0.6088 0.11119 0.10176 -0.1148 0.5389 0.9996
6.250 0.6369 0.11459 0.10507 -0.1153 0.5322 0.9996
6.500 0.6315 0.11631 0.10674 -0.1142 0.5227 0.9996
6.750 0.6506 0.11896 0.10932 -0.1140 0.5137 0.9996
7.000 0.6923 0.12444 0.11472 -0.1152 0.5098 0.9996
7.250 0.6641 0.12356 0.11382 -0.1131 0.4964 0.9996
7.500 0.6928 0.12746 0.11766 -0.1135 0.4913 0.9996
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Polar data table (+)
Polar graphs
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