NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S828 Airfoil (s828-nr) Reynolds number: 500,000 Max Cl/Cd: 82.04 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s828-nr-500000-n5.txt Download as CSV file: xf-s828-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S828 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
------ -------- --------- --------- -------- -------- --------
-11.250 -0.5170 0.04172 0.03772 -0.1090 0.7886 0.0026
-11.000 -0.5541 0.03630 0.03187 -0.1034 0.7854 0.0025
-10.750 -0.5693 0.03298 0.02819 -0.0989 0.7826 0.0025
-10.500 -0.5748 0.03047 0.02535 -0.0952 0.7799 0.0024
-10.250 -0.5782 0.02775 0.02224 -0.0913 0.7775 0.0025
-10.000 -0.5704 0.02620 0.02043 -0.0889 0.7754 0.0025
-9.750 -0.5600 0.02443 0.01837 -0.0868 0.7732 0.0025
-9.500 -0.5461 0.02293 0.01663 -0.0851 0.7713 0.0026
-9.250 -0.5291 0.02182 0.01535 -0.0839 0.7694 0.0026
-9.000 -0.5109 0.02066 0.01399 -0.0828 0.7676 0.0027
-8.750 -0.4917 0.01965 0.01281 -0.0818 0.7660 0.0029
-8.500 -0.4721 0.01884 0.01187 -0.0809 0.7644 0.0029
-8.250 -0.4523 0.01806 0.01095 -0.0799 0.7630 0.0030
-8.000 -0.4320 0.01739 0.01017 -0.0790 0.7617 0.0032
-7.750 -0.4115 0.01676 0.00942 -0.0781 0.7604 0.0036
-7.500 -0.3907 0.01624 0.00884 -0.0773 0.7589 0.0036
-7.250 -0.3708 0.01560 0.00812 -0.0763 0.7575 0.0038
-7.000 -0.3499 0.01511 0.00758 -0.0755 0.7561 0.0043
-6.750 -0.3283 0.01471 0.00714 -0.0748 0.7548 0.0050
-6.500 -0.3067 0.01432 0.00668 -0.0740 0.7535 0.0055
-6.250 -0.2848 0.01399 0.00629 -0.0733 0.7523 0.0059
-6.000 -0.2636 0.01360 0.00587 -0.0725 0.7511 0.0081
-5.750 -0.2422 0.01325 0.00550 -0.0716 0.7499 0.0104
-5.500 -0.2211 0.01292 0.00515 -0.0707 0.7488 0.0151
-5.250 -0.2000 0.01261 0.00486 -0.0698 0.7476 0.0242
-5.000 -0.1797 0.01227 0.00461 -0.0688 0.7465 0.0407
-4.750 -0.1595 0.01197 0.00438 -0.0678 0.7454 0.0613
-4.500 -0.1408 0.01163 0.00419 -0.0665 0.7443 0.0929
-4.250 -0.1227 0.01131 0.00401 -0.0650 0.7432 0.1297
-4.000 -0.1069 0.01095 0.00384 -0.0631 0.7420 0.1803
-3.750 -0.0935 0.01057 0.00368 -0.0607 0.7409 0.2419
-3.500 -0.0852 0.01006 0.00351 -0.0573 0.7397 0.3304
-3.250 -0.0820 0.00944 0.00330 -0.0529 0.7385 0.4391
-3.000 -0.0818 0.00878 0.00307 -0.0477 0.7373 0.5504
-2.750 -0.0823 0.00806 0.00296 -0.0420 0.7362 0.6906
-2.500 -0.0573 0.00819 0.00334 -0.0411 0.7355 0.7704
-2.250 -0.0318 0.00830 0.00342 -0.0408 0.7347 0.7914
-2.000 -0.0058 0.00844 0.00350 -0.0405 0.7338 0.8057
-1.750 0.0191 0.00861 0.00362 -0.0400 0.7329 0.8184
-1.500 0.0457 0.00902 0.00404 -0.0395 0.7321 0.8326
-1.250 0.0776 0.00961 0.00464 -0.0400 0.7314 0.8422
-1.000 0.1028 0.00970 0.00470 -0.0396 0.7305 0.8469
-0.750 0.1311 0.00975 0.00473 -0.0400 0.7297 0.8479
-0.500 0.1590 0.00979 0.00475 -0.0404 0.7289 0.8489
-0.250 0.1865 0.00982 0.00476 -0.0407 0.7281 0.8501
0.000 0.2138 0.00984 0.00477 -0.0409 0.7273 0.8513
0.250 0.2407 0.00986 0.00477 -0.0411 0.7265 0.8527
0.500 0.2673 0.00986 0.00476 -0.0413 0.7256 0.8542
0.750 0.2936 0.00985 0.00473 -0.0414 0.7247 0.8559
1.000 0.3198 0.00982 0.00469 -0.0415 0.7237 0.8576
1.250 0.3458 0.00978 0.00464 -0.0417 0.7230 0.8593
1.500 0.3734 0.00980 0.00466 -0.0420 0.7223 0.8603
1.750 0.4015 0.00984 0.00471 -0.0425 0.7216 0.8610
2.000 0.4296 0.00987 0.00476 -0.0429 0.7209 0.8616
2.250 0.4579 0.00992 0.00482 -0.0434 0.7202 0.8623
2.500 0.4858 0.00997 0.00489 -0.0438 0.7193 0.8630
2.750 0.5113 0.01003 0.00501 -0.0438 0.7183 0.8640
3.000 0.5364 0.01008 0.00512 -0.0436 0.7167 0.8651
3.250 0.5616 0.01012 0.00522 -0.0435 0.7148 0.8662
3.500 0.5874 0.01015 0.00529 -0.0435 0.7130 0.8673
3.750 0.6152 0.01002 0.00517 -0.0438 0.7087 0.8683
4.000 0.6383 0.00982 0.00501 -0.0430 0.7005 0.8695
4.250 0.6640 0.00959 0.00474 -0.0427 0.6912 0.8707
4.500 0.6830 0.00953 0.00476 -0.0412 0.6834 0.8723
4.750 0.7064 0.00944 0.00468 -0.0406 0.6757 0.8737
5.000 0.7259 0.00940 0.00472 -0.0392 0.6659 0.8748
5.250 0.7449 0.00939 0.00479 -0.0376 0.6557 0.8758
5.500 0.7614 0.00938 0.00482 -0.0355 0.6402 0.8770
5.750 0.7679 0.00936 0.00475 -0.0313 0.6087 0.8786
6.000 0.7513 0.00979 0.00490 -0.0225 0.5523 0.8816
6.250 0.7313 0.01076 0.00558 -0.0138 0.4958 0.8852
6.500 0.7137 0.01193 0.00648 -0.0063 0.4407 0.8884
6.750 0.6980 0.01323 0.00754 0.0006 0.3846 0.8908
7.000 0.6936 0.01434 0.00847 0.0053 0.3403 0.8929
7.250 0.6905 0.01550 0.00943 0.0095 0.2917 0.8951
7.500 0.6904 0.01662 0.01033 0.0131 0.2433 0.8972
7.750 0.6950 0.01760 0.01111 0.0159 0.2015 0.8992
8.000 0.7012 0.01856 0.01188 0.0183 0.1620 0.9012
8.250 0.7109 0.01938 0.01257 0.0203 0.1319 0.9028
8.500 0.7227 0.02010 0.01322 0.0220 0.1099 0.9042
8.750 0.7347 0.02083 0.01387 0.0235 0.0894 0.9056
9.000 0.7469 0.02159 0.01457 0.0251 0.0701 0.9071
9.250 0.7612 0.02225 0.01521 0.0263 0.0585 0.9086
9.500 0.7757 0.02293 0.01587 0.0274 0.0481 0.9101
9.750 0.7898 0.02365 0.01656 0.0286 0.0396 0.9117
10.000 0.8046 0.02436 0.01727 0.0296 0.0326 0.9133
10.250 0.8196 0.02507 0.01799 0.0306 0.0271 0.9148
10.500 0.8342 0.02581 0.01873 0.0316 0.0233 0.9164
10.750 0.8484 0.02653 0.01952 0.0327 0.0201 0.9181
11.000 0.8631 0.02724 0.02029 0.0337 0.0182 0.9199
11.250 0.8764 0.02807 0.02113 0.0347 0.0153 0.9217
11.500 0.8912 0.02882 0.02194 0.0356 0.0134 0.9235
11.750 0.9051 0.02965 0.02278 0.0364 0.0110 0.9254
12.000 0.9189 0.03052 0.02368 0.0373 0.0094 0.9273
12.250 0.9331 0.03137 0.02460 0.0381 0.0083 0.9292
12.500 0.9458 0.03232 0.02556 0.0390 0.0066 0.9311
12.750 0.9592 0.03322 0.02655 0.0398 0.0054 0.9332
13.000 0.9717 0.03421 0.02761 0.0406 0.0048 0.9355
13.250 0.9827 0.03534 0.02880 0.0416 0.0035 0.9381
13.500 0.9942 0.03647 0.03001 0.0424 0.0031 0.9408
14.000 1.0153 0.03898 0.03268 0.0440 0.0023 0.9470
14.250 1.0267 0.04027 0.03408 0.0445 0.0024 0.9510
14.500 1.0362 0.04182 0.03576 0.0450 0.0021 0.9551
14.750 1.0476 0.04338 0.03743 0.0451 0.0019 0.9592
15.000 1.0585 0.04515 0.03932 0.0449 0.0016 0.9634
15.250 1.0695 0.04702 0.04134 0.0445 0.0017 0.9682
15.500 1.0750 0.04954 0.04400 0.0442 0.0012 0.9735
15.750 1.0853 0.05162 0.04620 0.0434 0.0013 0.9812
16.000 1.0889 0.05386 0.04858 0.0437 0.0013 1.0000
16.250 1.0912 0.05632 0.05116 0.0440 0.0012 1.0000
16.500 1.0914 0.05909 0.05407 0.0442 0.0012 1.0000
16.750 1.0921 0.06186 0.05698 0.0442 0.0011 1.0000
17.000 1.0892 0.06517 0.06043 0.0441 0.0011 1.0000
17.250 1.0865 0.06857 0.06398 0.0437 0.0010 1.0000
17.500 1.0855 0.07186 0.06739 0.0431 0.0010 1.0000
17.750 1.0762 0.07642 0.07213 0.0422 0.0010 1.0000
18.000 1.0693 0.08081 0.07667 0.0411 0.0009 1.0000
18.250 1.0589 0.08590 0.08193 0.0394 0.0009 1.0000
18.500 1.0496 0.09107 0.08724 0.0375 0.0009 1.0000
18.750 1.0332 0.09766 0.09401 0.0347 0.0009 1.0000
19.000 1.0212 0.10373 0.10024 0.0319 0.0009 1.0000
19.250 1.0081 0.11025 0.10692 0.0286 0.0009 1.0000
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