NREL's S821 Airfoil (s821-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S821 Airfoil (s821-nr) Reynolds number: 100,000 Max Cl/Cd: 37.4 at α=8.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s821-nr-100000-n5.txt Download as CSV file: xf-s821-nr-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S821 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
------ -------- --------- --------- -------- -------- --------
-6.000 -0.0279 0.10296 0.09557 -0.0518 0.9504 0.2139
-5.750 -0.0197 0.09904 0.09161 -0.0554 0.9441 0.2167
-5.500 -0.0379 0.09315 0.08566 -0.0581 0.9319 0.2195
-5.250 -0.0084 0.09144 0.08399 -0.0604 0.9260 0.2202
-5.000 0.0091 0.09005 0.08267 -0.0603 0.9129 0.2209
-4.750 0.0288 0.08821 0.08087 -0.0614 0.9028 0.2218
-4.250 0.0667 0.08434 0.07706 -0.0638 0.8816 0.2248
-3.750 0.0868 0.07754 0.07022 -0.0687 0.8615 0.2296
-3.250 0.1052 0.06954 0.06213 -0.0753 0.8412 0.2340
-2.250 0.1525 0.05494 0.04727 -0.0895 0.7934 0.2457
-2.000 -0.0591 0.03189 0.02310 -0.0989 0.7681 0.2622
-1.750 -0.0226 0.03162 0.02289 -0.1002 0.7584 0.2634
-1.500 0.0069 0.03134 0.02266 -0.1006 0.7467 0.2647
-1.250 0.0437 0.03087 0.02220 -0.1025 0.7372 0.2664
-1.000 0.0671 0.03021 0.02152 -0.1030 0.7247 0.2685
-0.750 0.1020 0.02906 0.02023 -0.1061 0.7151 0.2716
-0.500 0.1237 0.02771 0.01870 -0.1077 0.7029 0.2749
-0.250 0.1603 0.02658 0.01734 -0.1110 0.6938 0.2779
0.000 0.1831 0.02646 0.01733 -0.1100 0.6819 0.2792
0.250 0.2150 0.02628 0.01718 -0.1106 0.6721 0.2809
0.500 0.2411 0.02610 0.01704 -0.1105 0.6616 0.2829
0.750 0.2699 0.02582 0.01675 -0.1110 0.6519 0.2852
1.000 0.3016 0.02544 0.01630 -0.1121 0.6430 0.2884
1.250 0.3288 0.02496 0.01572 -0.1129 0.6323 0.2920
1.500 0.3622 0.02461 0.01528 -0.1141 0.6238 0.2951
1.750 0.3860 0.02464 0.01544 -0.1133 0.6141 0.2972
2.000 0.4137 0.02461 0.01548 -0.1132 0.6052 0.2996
2.250 0.4446 0.02452 0.01537 -0.1137 0.5973 0.3027
2.500 0.4700 0.02437 0.01526 -0.1135 0.5876 0.3059
2.750 0.5023 0.02411 0.01488 -0.1145 0.5795 0.3100
3.000 0.5306 0.02404 0.01484 -0.1147 0.5714 0.3131
3.250 0.5553 0.02413 0.01505 -0.1139 0.5626 0.3158
3.500 0.5854 0.02418 0.01512 -0.1141 0.5550 0.3194
3.750 0.6113 0.02422 0.01522 -0.1138 0.5465 0.3234
4.000 0.6395 0.02415 0.01512 -0.1139 0.5376 0.3283
4.250 0.6704 0.02414 0.01508 -0.1143 0.5297 0.3321
4.500 0.6913 0.02427 0.01538 -0.1129 0.5196 0.3351
4.750 0.7187 0.02433 0.01545 -0.1125 0.5106 0.3390
5.000 0.7432 0.02441 0.01558 -0.1118 0.5009 0.3436
5.250 0.7699 0.02441 0.01552 -0.1116 0.4907 0.3491
5.500 0.7940 0.02453 0.01573 -0.1107 0.4811 0.3528
5.750 0.8153 0.02468 0.01601 -0.1093 0.4706 0.3568
6.000 0.8407 0.02480 0.01612 -0.1086 0.4609 0.3618
6.250 0.8620 0.02492 0.01629 -0.1074 0.4497 0.3673
6.500 0.8861 0.02503 0.01639 -0.1065 0.4394 0.3721
6.750 0.9036 0.02525 0.01676 -0.1046 0.4277 0.3761
7.000 0.9246 0.02544 0.01698 -0.1031 0.4169 0.3813
7.250 0.9420 0.02563 0.01722 -0.1013 0.4048 0.3869
7.500 0.9599 0.02583 0.01743 -0.0995 0.3931 0.3923
7.750 0.9748 0.02610 0.01778 -0.0972 0.3808 0.3965
8.000 0.9889 0.02646 0.01824 -0.0949 0.3678 0.4015
8.250 1.0041 0.02685 0.01863 -0.0928 0.3544 0.4073
8.500 1.0187 0.02731 0.01905 -0.0909 0.3395 0.4134
8.750 1.0302 0.02785 0.01971 -0.0884 0.3238 0.4176
9.000 1.0409 0.02849 0.02040 -0.0860 0.3072 0.4226
9.250 1.0510 0.02923 0.02113 -0.0836 0.2896 0.4283
9.500 1.0601 0.03009 0.02192 -0.0814 0.2714 0.4343
9.750 1.0667 0.03109 0.02290 -0.0790 0.2537 0.4389
10.000 1.0717 0.03225 0.02406 -0.0766 0.2371 0.4435
10.250 1.0760 0.03358 0.02535 -0.0744 0.2217 0.4488
10.500 1.0800 0.03506 0.02678 -0.0724 0.2078 0.4547
11.000 1.0872 0.03833 0.03006 -0.0690 0.1834 0.4648
11.250 1.0908 0.04012 0.03189 -0.0676 0.1730 0.4700
11.500 1.0932 0.04212 0.03388 -0.0664 0.1639 0.4758
11.750 1.0976 0.04413 0.03589 -0.0655 0.1549 0.4823
12.000 1.1009 0.04623 0.03806 -0.0647 0.1471 0.4873
12.250 1.1029 0.04853 0.04040 -0.0639 0.1401 0.4927
12.500 1.1073 0.05077 0.04271 -0.0635 0.1331 0.4991
12.750 1.1093 0.05334 0.04525 -0.0632 0.1273 0.5056
13.000 1.1139 0.05571 0.04774 -0.0630 0.1210 0.5113
13.250 1.1153 0.05843 0.05049 -0.0629 0.1161 0.5171
13.500 1.1202 0.06097 0.05314 -0.0629 0.1106 0.5242
13.750 1.1223 0.06389 0.05604 -0.0633 0.1061 0.5314
14.000 1.1262 0.06660 0.05890 -0.0634 0.1013 0.5373
14.250 1.1283 0.06959 0.06193 -0.0638 0.0973 0.5441
14.500 1.1320 0.07255 0.06495 -0.0643 0.0932 0.5521
14.750 1.1343 0.07566 0.06815 -0.0649 0.0894 0.5588
15.000 1.1367 0.07880 0.07135 -0.0655 0.0861 0.5662
15.250 1.1395 0.08204 0.07469 -0.0663 0.0824 0.5746
15.500 1.1411 0.08537 0.07805 -0.0672 0.0797 0.5819
15.750 1.1438 0.08871 0.08153 -0.0680 0.0764 0.5901
16.000 1.1461 0.09217 0.08504 -0.0691 0.0736 0.5993
16.250 1.1480 0.09561 0.08857 -0.0702 0.0711 0.6074
16.500 1.1495 0.09926 0.09235 -0.0714 0.0684 0.6169
16.750 1.1512 0.10285 0.09600 -0.0728 0.0661 0.6264
17.000 1.1526 0.10657 0.09984 -0.0742 0.0639 0.6363
17.250 1.1538 0.11038 0.10378 -0.0758 0.0616 0.6469
17.500 1.1554 0.11403 0.10749 -0.0773 0.0597 0.6582
17.750 1.1563 0.11790 0.11148 -0.0790 0.0578 0.6702
18.000 1.1554 0.12213 0.11588 -0.0810 0.0559 0.6828
18.250 1.1563 0.12593 0.11976 -0.0829 0.0543 0.6970
18.500 1.1581 0.12958 0.12348 -0.0846 0.0528 0.7136
18.750 1.1539 0.13447 0.12861 -0.0873 0.0511 0.7298
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