NREL's S817 Airfoil (s817-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S817 Airfoil (s817-nr) Reynolds number: 500,000 Max Cl/Cd: 101.1 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s817-nr-500000-n5.txt Download as CSV file: xf-s817-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S817 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 -0.2203 0.07541 0.07180 -0.1079 0.7338 0.0053
-9.500 -0.2686 0.06308 0.05935 -0.1117 0.7310 0.0040
-9.250 -0.2830 0.06000 0.05620 -0.1107 0.7296 0.0040
-9.000 -0.2989 0.05718 0.05329 -0.1086 0.7282 0.0040
-8.750 -0.3113 0.05503 0.05108 -0.1055 0.7269 0.0039
-8.500 -0.3193 0.05215 0.04809 -0.1030 0.7255 0.0039
-8.250 -0.3232 0.04917 0.04499 -0.1006 0.7240 0.0038
-8.000 -0.3237 0.04613 0.04180 -0.0982 0.7226 0.0038
-7.750 -0.3212 0.04309 0.03859 -0.0959 0.7214 0.0038
-7.500 -0.3184 0.03948 0.03475 -0.0931 0.7202 0.0037
-7.250 -0.3140 0.03534 0.03031 -0.0899 0.7191 0.0038
-7.000 -0.3065 0.03089 0.02551 -0.0868 0.7181 0.0038
-6.750 -0.2967 0.02067 0.01421 -0.0822 0.7172 0.0043
-6.500 -0.2728 0.01952 0.01288 -0.0820 0.7163 0.0045
-6.250 -0.2469 0.01826 0.01141 -0.0819 0.7155 0.0046
-6.000 -0.2213 0.01752 0.01053 -0.0819 0.7146 0.0049
-5.750 -0.1954 0.01681 0.00968 -0.0819 0.7138 0.0053
-5.500 -0.1697 0.01609 0.00885 -0.0818 0.7130 0.0059
-5.250 -0.1447 0.01556 0.00821 -0.0816 0.7121 0.0063
-5.000 -0.1227 0.01472 0.00731 -0.0808 0.7111 0.0067
-4.750 -0.1012 0.01417 0.00673 -0.0800 0.7101 0.0070
-4.500 -0.0800 0.01371 0.00623 -0.0792 0.7089 0.0073
-4.250 -0.0589 0.01329 0.00577 -0.0783 0.7079 0.0080
-4.000 -0.0374 0.01291 0.00534 -0.0775 0.7070 0.0088
-3.750 -0.0162 0.01251 0.00492 -0.0766 0.7060 0.0105
-3.500 0.0071 0.01225 0.00461 -0.0761 0.7052 0.0126
-3.250 0.0309 0.01202 0.00439 -0.0758 0.7043 0.0166
-3.000 0.0547 0.01178 0.00414 -0.0755 0.7035 0.0206
-2.750 0.0793 0.01157 0.00391 -0.0752 0.7027 0.0261
-2.500 0.1038 0.01135 0.00372 -0.0750 0.7020 0.0399
-2.250 0.1287 0.01115 0.00358 -0.0749 0.7011 0.0639
-2.000 0.1538 0.01095 0.00344 -0.0748 0.7003 0.0958
-1.750 0.1547 0.00861 0.00283 -0.0717 0.6992 0.6205
-1.500 0.1811 0.00868 0.00303 -0.0715 0.6984 0.6862
-1.250 0.2089 0.00880 0.00316 -0.0717 0.6977 0.7037
-1.000 0.2372 0.00890 0.00321 -0.0721 0.6969 0.7131
-0.750 0.2653 0.00899 0.00330 -0.0724 0.6961 0.7187
-0.500 0.2937 0.00908 0.00335 -0.0728 0.6952 0.7250
-0.250 0.3219 0.00915 0.00340 -0.0732 0.6943 0.7292
0.000 0.3503 0.00919 0.00343 -0.0736 0.6933 0.7310
0.250 0.3789 0.00921 0.00343 -0.0742 0.6923 0.7318
0.500 0.4075 0.00924 0.00345 -0.0747 0.6915 0.7326
0.750 0.4361 0.00928 0.00347 -0.0753 0.6907 0.7335
1.000 0.4648 0.00932 0.00350 -0.0758 0.6899 0.7345
1.250 0.4934 0.00936 0.00354 -0.0764 0.6891 0.7356
1.500 0.5221 0.00940 0.00358 -0.0770 0.6883 0.7368
1.750 0.5509 0.00944 0.00362 -0.0776 0.6874 0.7379
2.000 0.5797 0.00950 0.00369 -0.0782 0.6867 0.7390
2.250 0.6085 0.00957 0.00376 -0.0788 0.6860 0.7400
2.500 0.6373 0.00965 0.00384 -0.0795 0.6853 0.7410
2.750 0.6650 0.00972 0.00396 -0.0799 0.6843 0.7420
3.000 0.6923 0.00977 0.00410 -0.0802 0.6832 0.7430
3.250 0.7196 0.00985 0.00424 -0.0806 0.6821 0.7440
3.500 0.7470 0.00993 0.00439 -0.0809 0.6810 0.7451
3.750 0.7744 0.01001 0.00455 -0.0813 0.6798 0.7462
4.000 0.8018 0.01002 0.00462 -0.0816 0.6773 0.7474
4.250 0.8308 0.00986 0.00446 -0.0820 0.6724 0.7486
4.500 0.8549 0.00973 0.00440 -0.0815 0.6647 0.7500
4.750 0.8803 0.00951 0.00421 -0.0812 0.6549 0.7515
5.000 0.9020 0.00934 0.00409 -0.0801 0.6388 0.7531
5.250 0.9233 0.00926 0.00402 -0.0790 0.6171 0.7548
5.500 0.9412 0.00931 0.00400 -0.0773 0.5803 0.7565
5.750 0.9393 0.00988 0.00425 -0.0716 0.5125 0.7584
6.000 0.9176 0.01088 0.00492 -0.0624 0.4465 0.7607
6.250 0.9019 0.01207 0.00587 -0.0549 0.3906 0.7631
6.500 0.8848 0.01356 0.00709 -0.0479 0.3304 0.7657
6.750 0.8743 0.01508 0.00836 -0.0426 0.2762 0.7682
7.000 0.8693 0.01656 0.00961 -0.0384 0.2271 0.7706
7.250 0.8679 0.01796 0.01082 -0.0350 0.1816 0.7727
7.500 0.8707 0.01922 0.01192 -0.0323 0.1445 0.7748
7.750 0.8770 0.02034 0.01292 -0.0301 0.1146 0.7770
8.000 0.8866 0.02132 0.01384 -0.0283 0.0941 0.7793
8.250 0.8984 0.02220 0.01468 -0.0269 0.0798 0.7818
8.500 0.9112 0.02304 0.01550 -0.0256 0.0686 0.7842
8.750 0.9251 0.02384 0.01629 -0.0245 0.0595 0.7866
9.000 0.9382 0.02466 0.01713 -0.0233 0.0520 0.7890
9.250 0.9514 0.02550 0.01799 -0.0221 0.0452 0.7918
9.500 0.9660 0.02628 0.01882 -0.0212 0.0412 0.7947
9.750 0.9800 0.02713 0.01969 -0.0202 0.0373 0.7977
10.000 0.9929 0.02806 0.02063 -0.0191 0.0335 0.8006
10.250 1.0081 0.02882 0.02149 -0.0183 0.0314 0.8034
10.500 1.0219 0.02970 0.02243 -0.0174 0.0289 0.8066
10.750 1.0347 0.03067 0.02344 -0.0164 0.0265 0.8101
11.000 1.0479 0.03164 0.02448 -0.0155 0.0246 0.8137
11.250 1.0617 0.03257 0.02550 -0.0146 0.0235 0.8172
11.500 1.0758 0.03348 0.02650 -0.0139 0.0219 0.8211
11.750 1.0892 0.03447 0.02749 -0.0131 0.0194 0.8255
12.250 1.1153 0.03652 0.02973 -0.0116 0.0167 0.8348
12.500 1.1295 0.03744 0.03063 -0.0111 0.0131 0.8405
12.750 1.1432 0.03844 0.03172 -0.0104 0.0113 0.8465
13.000 1.1550 0.03958 0.03289 -0.0097 0.0092 0.8538
13.250 1.1670 0.04072 0.03415 -0.0090 0.0083 0.8618
13.500 1.1783 0.04192 0.03542 -0.0082 0.0071 0.8717
13.750 1.1884 0.04316 0.03678 -0.0073 0.0062 0.8840
14.250 1.2103 0.04587 0.03980 -0.0062 0.0043 0.9451
14.750 1.2280 0.04920 0.04328 -0.0054 0.0021 1.0000
15.000 1.2339 0.05119 0.04535 -0.0047 0.0014 1.0000
15.250 1.2425 0.05297 0.04725 -0.0043 0.0013 1.0000
15.500 1.2493 0.05496 0.04934 -0.0039 0.0012 1.0000
15.750 1.2542 0.05719 0.05168 -0.0035 0.0010 1.0000
16.000 1.2578 0.05961 0.05424 -0.0031 0.0008 1.0000
16.250 1.2638 0.06182 0.05657 -0.0029 0.0009 1.0000
16.500 1.2641 0.06475 0.05965 -0.0027 0.0007 1.0000
16.750 1.2656 0.06761 0.06266 -0.0026 0.0007 1.0000
17.000 1.2680 0.07042 0.06561 -0.0028 0.0007 1.0000
17.250 1.2661 0.07386 0.06922 -0.0030 0.0006 1.0000
17.500 1.2662 0.07711 0.07261 -0.0035 0.0007 1.0000
17.750 1.2629 0.08094 0.07660 -0.0041 0.0006 1.0000
18.000 1.2560 0.08543 0.08127 -0.0051 0.0006 1.0000
18.250 1.2505 0.08984 0.08584 -0.0063 0.0006 1.0000
18.500 1.2420 0.09486 0.09103 -0.0078 0.0005 1.0000
18.750 1.2311 0.10045 0.09679 -0.0099 0.0005 1.0000
19.000 1.2188 0.10652 0.10305 -0.0124 0.0005 1.0000
19.250 1.2035 0.11340 0.11011 -0.0155 0.0005 1.0000
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