NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S828 Airfoil (s828-nr) Reynolds number: 500,000 Max Cl/Cd: 76.86 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s828-nr-500000.txt Download as CSV file: xf-s828-nr-500000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.2666 0.08961 0.08666 -0.1041 0.8412 0.0159
-11.500 -0.2725 0.08439 0.08144 -0.1067 0.8379 0.0158
-8.250 -0.4683 0.02731 0.02163 -0.0794 0.8008 0.0082
-8.000 -0.4531 0.02386 0.01775 -0.0775 0.7992 0.0075
-7.750 -0.4171 0.02046 0.01386 -0.0792 0.7980 0.0071
-7.500 -0.3841 0.01890 0.01209 -0.0805 0.7968 0.0071
-7.250 -0.3567 0.01781 0.01086 -0.0808 0.7954 0.0072
-7.000 -0.3330 0.01701 0.00996 -0.0804 0.7939 0.0078
-6.750 -0.3100 0.01645 0.00931 -0.0798 0.7925 0.0088
-6.500 -0.2920 0.01543 0.00820 -0.0783 0.7913 0.0096
-6.250 -0.2722 0.01491 0.00761 -0.0773 0.7900 0.0103
-6.000 -0.2510 0.01454 0.00721 -0.0764 0.7889 0.0123
-5.750 -0.2314 0.01405 0.00672 -0.0753 0.7876 0.0151
-5.500 -0.2125 0.01353 0.00620 -0.0739 0.7863 0.0222
-5.250 -0.1953 0.01297 0.00577 -0.0723 0.7850 0.0491
-5.000 -0.1776 0.01255 0.00554 -0.0708 0.7837 0.0859
-4.750 -0.1620 0.01210 0.00532 -0.0690 0.7824 0.1386
-4.500 -0.1514 0.01153 0.00512 -0.0663 0.7812 0.2227
-4.250 -0.1491 0.01092 0.00494 -0.0618 0.7798 0.3296
-4.000 -0.1571 0.01021 0.00475 -0.0552 0.7783 0.4578
-3.750 -0.1693 0.00938 0.00453 -0.0474 0.7767 0.6027
-3.500 -0.1577 0.00929 0.00513 -0.0435 0.7757 0.7705
-3.250 -0.1365 0.00962 0.00542 -0.0420 0.7748 0.8008
-3.000 -0.1150 0.00998 0.00573 -0.0406 0.7738 0.8182
-2.750 -0.0829 0.01053 0.00625 -0.0412 0.7730 0.8269
-2.500 -0.0555 0.01093 0.00660 -0.0411 0.7721 0.8344
-2.250 -0.0203 0.01153 0.00717 -0.0423 0.7713 0.8398
-2.000 0.0048 0.01190 0.00748 -0.0417 0.7703 0.8472
-1.750 0.0483 0.01262 0.00817 -0.0445 0.7698 0.8498
-1.500 0.0806 0.01341 0.00894 -0.0449 0.7690 0.8601
-1.250 0.1503 0.01442 0.00989 -0.0526 0.7689 0.8614
-1.000 0.1955 0.01466 0.01010 -0.0563 0.7683 0.8621
-0.750 0.2342 0.01477 0.01018 -0.0589 0.7676 0.8630
-0.500 0.2694 0.01486 0.01025 -0.0608 0.7669 0.8642
-0.250 0.3015 0.01494 0.01032 -0.0621 0.7662 0.8657
0.000 0.3262 0.01501 0.01037 -0.0619 0.7654 0.8687
0.250 0.3230 0.01497 0.01033 -0.0560 0.7642 0.8757
0.500 0.3579 0.01501 0.01036 -0.0579 0.7635 0.8764
0.750 0.3912 0.01505 0.01040 -0.0595 0.7628 0.8772
1.000 0.4228 0.01512 0.01048 -0.0607 0.7621 0.8783
1.250 0.4518 0.01523 0.01059 -0.0615 0.7614 0.8796
1.500 0.4651 0.01538 0.01079 -0.0591 0.7598 0.8830
1.750 0.4453 0.01542 0.01089 -0.0498 0.7567 0.8901
2.000 0.4726 0.01549 0.01100 -0.0502 0.7551 0.8910
2.250 0.5005 0.01555 0.01109 -0.0508 0.7538 0.8921
2.500 0.5255 0.01559 0.01116 -0.0507 0.7524 0.8934
2.750 0.5477 0.01558 0.01117 -0.0500 0.7511 0.8951
3.000 0.5606 0.01549 0.01110 -0.0473 0.7496 0.8984
3.250 0.5620 0.01523 0.01083 -0.0424 0.7479 0.9030
3.500 0.5752 0.01535 0.01103 -0.0399 0.7433 0.9043
3.750 0.6083 0.01487 0.01057 -0.0410 0.7389 0.9048
4.000 0.6591 0.01397 0.00960 -0.0454 0.7341 0.9044
4.250 0.6777 0.01374 0.00943 -0.0437 0.7273 0.9057
4.500 0.7122 0.01329 0.00898 -0.0450 0.7222 0.9063
4.750 0.7392 0.01301 0.00874 -0.0450 0.7167 0.9073
5.000 0.7565 0.01276 0.00855 -0.0431 0.7109 0.9091
5.250 0.7894 0.01237 0.00815 -0.0442 0.7053 0.9098
5.500 0.7891 0.01218 0.00806 -0.0389 0.6996 0.9134
5.750 0.8107 0.01176 0.00763 -0.0378 0.6919 0.9157
6.000 0.8178 0.01150 0.00747 -0.0337 0.6828 0.9175
6.250 0.8311 0.01125 0.00730 -0.0309 0.6728 0.9191
6.500 0.8366 0.01103 0.00714 -0.0264 0.6592 0.9213
6.750 0.8297 0.01081 0.00697 -0.0194 0.6426 0.9250
7.000 0.8247 0.01073 0.00683 -0.0132 0.6075 0.9287
7.250 0.8039 0.01117 0.00693 -0.0041 0.5438 0.9324
7.500 0.7792 0.01221 0.00767 0.0049 0.4857 0.9367
7.750 0.7611 0.01342 0.00864 0.0120 0.4334 0.9413
8.000 0.7469 0.01476 0.00973 0.0179 0.3807 0.9446
8.250 0.7374 0.01603 0.01078 0.0230 0.3289 0.9479
8.500 0.7329 0.01726 0.01178 0.0271 0.2788 0.9511
8.750 0.7316 0.01846 0.01273 0.0305 0.2281 0.9543
9.000 0.7325 0.01960 0.01362 0.0335 0.1784 0.9575
9.250 0.7397 0.02057 0.01443 0.0356 0.1408 0.9602
9.500 0.7493 0.02151 0.01522 0.0372 0.1077 0.9627
9.750 0.7602 0.02242 0.01601 0.0386 0.0816 0.9654
10.000 0.7714 0.02337 0.01685 0.0399 0.0601 0.9682
10.250 0.7849 0.02427 0.01769 0.0408 0.0459 0.9708
10.500 0.8015 0.02527 0.01869 0.0410 0.0370 0.9728
10.750 0.8166 0.02643 0.01983 0.0412 0.0301 0.9749
11.000 0.8364 0.02729 0.02080 0.0409 0.0274 0.9769
11.250 0.8554 0.02824 0.02176 0.0406 0.0234 0.9790
11.500 0.8713 0.02945 0.02303 0.0405 0.0202 0.9814
11.750 0.8944 0.03019 0.02379 0.0396 0.0171 0.9835
12.000 0.9106 0.03152 0.02516 0.0392 0.0141 0.9853
12.250 0.9310 0.03253 0.02624 0.0385 0.0124 0.9873
12.500 0.9457 0.03396 0.02768 0.0382 0.0099 0.9897
12.750 0.9654 0.03494 0.02877 0.0376 0.0083 0.9927
13.250 0.9860 0.03778 0.03173 0.0388 0.0054 1.0000
13.500 0.9921 0.03913 0.03316 0.0402 0.0051 1.0000
13.750 0.9959 0.04088 0.03495 0.0415 0.0044 1.0000
14.000 1.0013 0.04261 0.03680 0.0426 0.0040 1.0000
14.250 1.0054 0.04454 0.03883 0.0436 0.0041 1.0000
14.500 1.0108 0.04647 0.04090 0.0445 0.0038 1.0000
14.750 1.0175 0.04831 0.04286 0.0450 0.0035 1.0000
15.000 1.0214 0.05048 0.04515 0.0457 0.0032 1.0000
15.250 1.0224 0.05300 0.04782 0.0465 0.0033 1.0000
15.500 1.0269 0.05520 0.05008 0.0465 0.0028 1.0000
15.750 1.0288 0.05777 0.05282 0.0469 0.0029 1.0000
16.000 1.0260 0.06095 0.05619 0.0473 0.0030 1.0000
16.250 1.0244 0.06406 0.05940 0.0472 0.0028 1.0000
16.500 1.0195 0.06773 0.06324 0.0470 0.0028 1.0000
16.750 1.0085 0.07232 0.06800 0.0466 0.0027 1.0000
17.000 1.0038 0.07630 0.07215 0.0458 0.0027 1.0000
17.250 0.9839 0.08259 0.07866 0.0444 0.0026 1.0000
17.500 0.9824 0.08647 0.08266 0.0429 0.0027 1.0000
17.750 0.9689 0.09244 0.08883 0.0408 0.0027 1.0000
18.000 0.9342 0.10233 0.09899 0.0368 0.0026 1.0000
18.250 0.9354 0.10636 0.10313 0.0345 0.0027 1.0000
18.500 0.9173 0.11415 0.11109 0.0305 0.0026 1.0000
18.750 0.9024 0.12180 0.11891 0.0263 0.0027 1.0000
19.000 0.8848 0.13035 0.12765 0.0215 0.0028 1.0000
19.250 0.8550 0.14246 0.14001 0.0149 0.0029 1.0000
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