NREL's S820 Airfoil (s820-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S820 Airfoil (s820-nr) Reynolds number: 1,000,000 Max Cl/Cd: 129.48 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s820-nr-1000000.txt Download as CSV file: xf-s820-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S820 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 -0.2736 0.08313 0.08081 -0.0982 0.8394 0.0071
-11.250 -0.2827 0.07567 0.07329 -0.1031 0.8336 0.0070
-11.000 -0.3001 0.06886 0.06638 -0.1069 0.8280 0.0071
-10.750 -0.3184 0.06421 0.06167 -0.1090 0.8228 0.0070
-10.500 -0.3339 0.05978 0.05710 -0.1099 0.8178 0.0071
-10.250 -0.3501 0.05629 0.05350 -0.1099 0.8130 0.0070
-10.000 -0.3652 0.05318 0.05030 -0.1093 0.8086 0.0070
-9.750 -0.3793 0.05025 0.04723 -0.1076 0.8043 0.0071
-9.500 -0.3915 0.04798 0.04482 -0.1055 0.8000 0.0071
-9.250 -0.4040 0.04575 0.04248 -0.1023 0.7965 0.0071
-9.000 -0.4133 0.04383 0.04043 -0.0987 0.7929 0.0071
-8.750 -0.4172 0.04145 0.03787 -0.0958 0.7896 0.0071
-8.500 -0.4184 0.03910 0.03528 -0.0930 0.7864 0.0071
-8.250 -0.4157 0.03683 0.03280 -0.0905 0.7837 0.0071
-8.000 -0.4256 0.03152 0.02722 -0.0874 0.7811 0.0075
-7.750 -0.4127 0.02979 0.02538 -0.0862 0.7787 0.0076
-7.500 -0.3980 0.02827 0.02372 -0.0851 0.7764 0.0078
-7.250 -0.3818 0.02674 0.02204 -0.0840 0.7742 0.0081
-7.000 -0.3637 0.02524 0.02037 -0.0830 0.7718 0.0085
-6.750 -0.3434 0.02371 0.01866 -0.0820 0.7696 0.0090
-6.500 -0.3190 0.02345 0.01817 -0.0810 0.7676 0.0101
-6.250 -0.2984 0.02276 0.01723 -0.0798 0.7654 0.0103
-5.250 -0.1932 0.01397 0.00793 -0.0784 0.7581 0.0065
-5.000 -0.1759 0.01254 0.00637 -0.0765 0.7558 0.0054
-4.750 -0.1552 0.01189 0.00566 -0.0754 0.7541 0.0051
-4.500 -0.1332 0.01137 0.00510 -0.0747 0.7522 0.0050
-4.250 -0.1108 0.01086 0.00453 -0.0740 0.7500 0.0050
-4.000 -0.0873 0.01041 0.00404 -0.0735 0.7479 0.0051
-3.750 -0.0627 0.01004 0.00362 -0.0732 0.7460 0.0055
-3.500 -0.0367 0.00979 0.00333 -0.0731 0.7441 0.0063
-3.250 -0.0103 0.00958 0.00305 -0.0731 0.7421 0.0079
-3.000 0.0145 0.00917 0.00277 -0.0729 0.7404 0.0409
-2.750 0.0201 0.00653 0.00194 -0.0709 0.7383 0.5453
-2.500 0.0473 0.00639 0.00198 -0.0710 0.7364 0.6116
-2.250 0.0756 0.00653 0.00217 -0.0711 0.7345 0.6465
-2.000 0.1046 0.00660 0.00221 -0.0715 0.7325 0.6561
-1.750 0.1338 0.00662 0.00220 -0.0720 0.7307 0.6596
-1.500 0.1633 0.00664 0.00216 -0.0725 0.7289 0.6616
-1.250 0.1927 0.00669 0.00215 -0.0731 0.7270 0.6636
-1.000 0.2220 0.00668 0.00213 -0.0737 0.7254 0.6655
-0.750 0.2510 0.00665 0.00210 -0.0742 0.7235 0.6677
-0.500 0.2801 0.00663 0.00208 -0.0747 0.7215 0.6696
-0.250 0.3093 0.00663 0.00208 -0.0752 0.7195 0.6716
0.000 0.3386 0.00664 0.00207 -0.0757 0.7177 0.6736
0.250 0.3679 0.00666 0.00208 -0.0763 0.7159 0.6758
0.500 0.3972 0.00670 0.00210 -0.0769 0.7140 0.6781
0.750 0.4265 0.00676 0.00213 -0.0774 0.7120 0.6801
1.000 0.4553 0.00674 0.00215 -0.0779 0.7101 0.6823
1.250 0.4841 0.00673 0.00217 -0.0784 0.7078 0.6845
1.500 0.5129 0.00671 0.00217 -0.0788 0.7048 0.6866
1.750 0.5416 0.00669 0.00214 -0.0792 0.7008 0.6889
2.000 0.5696 0.00667 0.00213 -0.0794 0.6951 0.6912
2.250 0.5976 0.00662 0.00208 -0.0796 0.6888 0.6936
2.500 0.6260 0.00665 0.00207 -0.0800 0.6837 0.6958
2.750 0.6537 0.00660 0.00210 -0.0802 0.6785 0.6985
3.000 0.6817 0.00659 0.00212 -0.0805 0.6734 0.7009
3.250 0.7097 0.00662 0.00216 -0.0808 0.6686 0.7033
3.500 0.7376 0.00663 0.00222 -0.0810 0.6626 0.7059
3.750 0.7648 0.00667 0.00224 -0.0811 0.6555 0.7084
4.000 0.7925 0.00669 0.00230 -0.0814 0.6478 0.7106
4.250 0.8193 0.00672 0.00236 -0.0814 0.6406 0.7134
4.500 0.8459 0.00676 0.00244 -0.0814 0.6304 0.7160
4.750 0.8723 0.00682 0.00253 -0.0814 0.6197 0.7187
5.000 0.8972 0.00694 0.00262 -0.0811 0.6039 0.7215
5.250 0.9206 0.00711 0.00275 -0.0804 0.5833 0.7244
5.500 0.9409 0.00735 0.00292 -0.0792 0.5494 0.7274
5.750 0.9492 0.00800 0.00329 -0.0758 0.4829 0.7306
6.000 0.9525 0.00882 0.00380 -0.0714 0.4150 0.7338
6.250 0.9552 0.00951 0.00424 -0.0669 0.3617 0.7372
6.500 0.9571 0.01016 0.00470 -0.0624 0.3176 0.7405
6.750 0.9616 0.01084 0.00523 -0.0585 0.2782 0.7441
7.000 0.9673 0.01154 0.00578 -0.0549 0.2416 0.7478
7.250 0.9748 0.01224 0.00634 -0.0519 0.2107 0.7516
7.500 0.9839 0.01292 0.00691 -0.0492 0.1833 0.7554
7.750 0.9940 0.01358 0.00750 -0.0468 0.1591 0.7595
8.000 1.0044 0.01429 0.00813 -0.0445 0.1377 0.7639
8.250 1.0171 0.01493 0.00873 -0.0426 0.1216 0.7683
8.500 1.0272 0.01571 0.00942 -0.0405 0.1024 0.7727
8.750 1.0414 0.01632 0.01003 -0.0390 0.0921 0.7775
9.000 1.0541 0.01704 0.01071 -0.0373 0.0795 0.7826
9.250 1.0681 0.01771 0.01137 -0.0359 0.0699 0.7877
9.500 1.0816 0.01841 0.01207 -0.0344 0.0620 0.7935
9.750 1.0952 0.01915 0.01280 -0.0330 0.0533 0.7997
10.000 1.1089 0.01985 0.01353 -0.0317 0.0457 0.8068
10.250 1.1222 0.02063 0.01430 -0.0303 0.0390 0.8147
10.750 1.1468 0.02228 0.01598 -0.0275 0.0262 0.8341
11.000 1.1596 0.02307 0.01684 -0.0262 0.0222 0.8469
11.250 1.1697 0.02401 0.01780 -0.0246 0.0168 0.8649
11.500 1.1797 0.02481 0.01874 -0.0227 0.0141 0.8963
11.750 1.1968 0.02560 0.01970 -0.0226 0.0116 1.0000
12.000 1.2091 0.02663 0.02073 -0.0216 0.0094 1.0000
12.250 1.2219 0.02764 0.02178 -0.0206 0.0080 1.0000
12.500 1.2345 0.02868 0.02284 -0.0197 0.0068 1.0000
12.750 1.2463 0.02978 0.02398 -0.0187 0.0057 1.0000
13.000 1.2560 0.03106 0.02527 -0.0177 0.0039 1.0000
13.250 1.2657 0.03239 0.02663 -0.0166 0.0026 1.0000
13.500 1.2753 0.03376 0.02807 -0.0157 0.0020 1.0000
13.750 1.2817 0.03543 0.02980 -0.0145 0.0013 1.0000
14.000 1.2914 0.03683 0.03128 -0.0137 0.0012 1.0000
14.250 1.3009 0.03828 0.03279 -0.0129 0.0010 1.0000
14.500 1.3056 0.04019 0.03478 -0.0119 0.0008 1.0000
14.750 1.3140 0.04181 0.03648 -0.0112 0.0007 1.0000
15.000 1.3170 0.04398 0.03876 -0.0103 0.0007 1.0000
15.250 1.3160 0.04667 0.04160 -0.0093 0.0006 1.0000
15.500 1.3216 0.04873 0.04374 -0.0089 0.0005 1.0000
15.750 1.3253 0.05102 0.04613 -0.0084 0.0005 1.0000
16.000 1.3248 0.05385 0.04909 -0.0080 0.0005 1.0000
16.250 1.3276 0.05639 0.05173 -0.0079 0.0005 1.0000
16.500 1.3254 0.05960 0.05507 -0.0077 0.0005 1.0000
16.750 1.3211 0.06319 0.05880 -0.0078 0.0005 1.0000
17.000 1.3209 0.06635 0.06205 -0.0082 0.0005 1.0000
17.250 1.3168 0.07015 0.06597 -0.0087 0.0005 1.0000
17.500 1.3116 0.07425 0.07020 -0.0095 0.0005 1.0000
17.750 1.3013 0.07927 0.07537 -0.0108 0.0005 1.0000
18.000 1.2885 0.08486 0.08112 -0.0125 0.0004 1.0000
18.250 1.2750 0.09086 0.08728 -0.0147 0.0004 1.0000
18.500 1.2716 0.09534 0.09186 -0.0165 0.0004 1.0000
18.750 1.2536 0.10259 0.09927 -0.0197 0.0004 1.0000
19.000 1.2400 0.10926 0.10609 -0.0230 0.0004 1.0000
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