NREL's S818 Airfoil (s818-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S818 Airfoil (s818-nr) Reynolds number: 100,000 Max Cl/Cd: 39.56 at α=9.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s818-nr-100000-n5.txt Download as CSV file: xf-s818-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S818 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.3519 0.11340 0.10638 -0.0283 1.0000 0.3419
-10.500 -0.3406 0.11259 0.10555 -0.0273 1.0000 0.3457
-10.250 -0.3441 0.11186 0.10481 -0.0261 1.0000 0.3542
-10.000 -0.3262 0.11101 0.10395 -0.0251 1.0000 0.3563
-9.750 -0.3147 0.11012 0.10305 -0.0239 1.0000 0.3588
-9.500 -0.3156 0.10958 0.10250 -0.0230 0.9996 0.3662
-9.250 -0.2874 0.10986 0.10273 -0.0261 0.9952 0.3834
-9.000 -0.2778 0.10774 0.10052 -0.0298 0.9903 0.3840
-8.750 -0.2354 0.10476 0.09747 -0.0331 0.9860 0.3852
-8.500 -0.1943 0.10242 0.09507 -0.0366 0.9822 0.3870
-8.250 -0.1645 0.10028 0.09287 -0.0396 0.9770 0.3883
-8.000 -0.1361 0.09821 0.09075 -0.0426 0.9714 0.3898
-7.750 -0.1066 0.09647 0.08895 -0.0458 0.9666 0.3938
-7.500 -0.1066 0.09552 0.08797 -0.0474 0.9570 0.3994
-7.250 -0.1179 0.09144 0.08379 -0.0499 0.9461 0.3839
-6.000 -0.0083 0.08109 0.07334 -0.0543 0.8810 0.3752
-5.750 0.0066 0.07880 0.07100 -0.0559 0.8662 0.3735
-5.500 0.0215 0.07630 0.06843 -0.0582 0.8515 0.3718
-5.250 0.0413 0.07377 0.06581 -0.0612 0.8366 0.3709
-5.000 0.0780 0.07164 0.06357 -0.0655 0.8209 0.3715
-4.750 0.1203 0.06931 0.06110 -0.0712 0.8034 0.3720
-4.500 0.1590 0.06652 0.05811 -0.0782 0.7835 0.3712
-4.250 0.1899 0.06400 0.05539 -0.0837 0.7606 0.3704
-4.000 0.2136 0.06199 0.05319 -0.0871 0.7374 0.3700
-3.750 0.2331 0.06024 0.05127 -0.0893 0.7160 0.3697
-3.500 0.2507 0.05875 0.04964 -0.0906 0.6973 0.3697
-3.250 0.2669 0.05743 0.04820 -0.0914 0.6800 0.3698
-3.000 0.2829 0.05625 0.04692 -0.0917 0.6643 0.3699
-2.750 0.3018 0.05539 0.04598 -0.0918 0.6498 0.3705
-2.500 0.3204 0.05462 0.04514 -0.0917 0.6367 0.3712
-2.250 0.3356 0.05371 0.04414 -0.0915 0.6251 0.3717
-2.000 0.3441 0.05267 0.04307 -0.0905 0.6138 0.3720
-1.750 0.3513 0.05154 0.04189 -0.0894 0.6042 0.3722
-1.500 0.3560 0.05041 0.04071 -0.0880 0.5952 0.3723
-1.250 0.3606 0.04936 0.03962 -0.0864 0.5872 0.3728
-1.000 0.3623 0.04831 0.03857 -0.0843 0.5796 0.3732
0.000 0.3247 0.03401 0.02379 -0.0906 0.5579 0.3846
0.250 0.3470 0.03352 0.02330 -0.0907 0.5515 0.3852
0.500 0.3702 0.03304 0.02281 -0.0911 0.5455 0.3860
0.750 0.3965 0.03255 0.02228 -0.0920 0.5405 0.3869
1.000 0.4205 0.03202 0.02174 -0.0927 0.5350 0.3880
1.250 0.4454 0.03146 0.02118 -0.0936 0.5294 0.3892
1.500 0.4733 0.03085 0.02051 -0.0952 0.5247 0.3906
1.750 0.5028 0.03015 0.01974 -0.0973 0.5202 0.3924
2.000 0.5321 0.02934 0.01889 -0.0997 0.5152 0.3946
2.250 0.5667 0.02842 0.01784 -0.1033 0.5109 0.3975
2.500 0.6049 0.02761 0.01684 -0.1074 0.5073 0.4006
2.750 0.6331 0.02770 0.01697 -0.1078 0.5041 0.4016
3.000 0.6577 0.02779 0.01719 -0.1076 0.5002 0.4027
3.250 0.6841 0.02788 0.01737 -0.1078 0.4966 0.4039
3.500 0.7120 0.02793 0.01747 -0.1083 0.4932 0.4053
3.750 0.7423 0.02794 0.01748 -0.1093 0.4901 0.4070
4.000 0.7739 0.02794 0.01747 -0.1107 0.4873 0.4087
4.250 0.8002 0.02795 0.01757 -0.1112 0.4838 0.4107
4.500 0.8294 0.02795 0.01761 -0.1124 0.4806 0.4129
4.750 0.8611 0.02793 0.01759 -0.1140 0.4778 0.4153
5.000 0.8921 0.02800 0.01768 -0.1153 0.4752 0.4173
5.250 0.9205 0.02823 0.01800 -0.1157 0.4730 0.4186
5.500 0.9509 0.02847 0.01831 -0.1164 0.4709 0.4201
5.750 0.9718 0.02881 0.01884 -0.1157 0.4678 0.4217
6.000 0.9941 0.02915 0.01934 -0.1152 0.4647 0.4237
6.250 1.0190 0.02949 0.01981 -0.1152 0.4620 0.4262
6.500 1.0464 0.02979 0.02020 -0.1157 0.4596 0.4290
6.750 1.0773 0.03005 0.02047 -0.1169 0.4573 0.4324
7.000 1.1075 0.03032 0.02083 -0.1177 0.4550 0.4346
7.250 1.1320 0.03075 0.02141 -0.1175 0.4526 0.4365
7.500 1.1465 0.03134 0.02226 -0.1157 0.4493 0.4384
7.750 1.1647 0.03185 0.02295 -0.1146 0.4457 0.4406
8.000 1.1878 0.03223 0.02347 -0.1143 0.4423 0.4431
8.250 1.2172 0.03249 0.02378 -0.1149 0.4393 0.4462
8.500 1.2514 0.03269 0.02396 -0.1164 0.4362 0.4499
8.750 1.2522 0.03348 0.02507 -0.1125 0.4311 0.4515
9.000 1.2675 0.03371 0.02547 -0.1106 0.4251 0.4538
9.250 1.2959 0.03341 0.02519 -0.1105 0.4180 0.4570
9.500 1.2911 0.03394 0.02593 -0.1057 0.4108 0.4594
9.750 1.3241 0.03347 0.02539 -0.1063 0.4034 0.4639
10.000 1.3189 0.03439 0.02652 -0.1019 0.3972 0.4666
10.250 1.3289 0.03480 0.02711 -0.0995 0.3908 0.4690
10.500 1.3481 0.03490 0.02730 -0.0982 0.3846 0.4720
10.750 1.3405 0.03613 0.02879 -0.0940 0.3778 0.4742
11.000 1.3597 0.03615 0.02885 -0.0929 0.3704 0.4779
11.250 1.3493 0.03777 0.03070 -0.0890 0.3632 0.4803
11.500 1.3563 0.03850 0.03151 -0.0870 0.3548 0.4841
11.750 1.3438 0.04058 0.03384 -0.0837 0.3468 0.4859
12.000 1.3440 0.04191 0.03531 -0.0816 0.3375 0.4886
12.250 1.3165 0.04584 0.03951 -0.0788 0.3284 0.4900
12.500 1.3017 0.04912 0.04296 -0.0773 0.3181 0.4923
12.750 1.2640 0.05538 0.04940 -0.0765 0.3073 0.4931
13.000 1.2049 0.06535 0.05955 -0.0775 0.2944 0.4920
13.250 1.1815 0.07146 0.06576 -0.0785 0.2785 0.4934
13.500 1.1909 0.07318 0.06747 -0.0786 0.2612 0.4978
13.750 1.2082 0.07367 0.06785 -0.0783 0.2400 0.5026
14.000 1.2118 0.07595 0.07002 -0.0782 0.2187 0.5059
14.250 1.2064 0.07964 0.07359 -0.0787 0.1997 0.5089
14.500 1.1981 0.08394 0.07779 -0.0795 0.1829 0.5119
14.750 1.1902 0.08840 0.08217 -0.0805 0.1679 0.5151
15.000 1.1836 0.09282 0.08654 -0.0817 0.1542 0.5184
15.250 1.1787 0.09703 0.09075 -0.0829 0.1420 0.5210
15.500 1.1757 0.10105 0.09477 -0.0840 0.1312 0.5242
15.750 1.1736 0.10496 0.09865 -0.0853 0.1218 0.5280
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