NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S828 Airfoil (s828-nr) Reynolds number: 200,000 Max Cl/Cd: 40.32 at α=7.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s828-nr-200000-n5.txt Download as CSV file: xf-s828-nr-200000-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 = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2893 0.09275 0.08869 -0.1011 0.8614 0.0074
-12.000 -0.2989 0.08653 0.08248 -0.1039 0.8577 0.0071
-11.750 -0.3176 0.07754 0.07353 -0.1087 0.8536 0.0072
-11.500 -0.3516 0.06527 0.06113 -0.1160 0.8494 0.0067
-11.250 -0.3846 0.05826 0.05391 -0.1174 0.8455 0.0066
-11.000 -0.4301 0.05078 0.04607 -0.1155 0.8405 0.0062
-10.750 -0.4557 0.04611 0.04100 -0.1122 0.8363 0.0059
-10.500 -0.4678 0.04348 0.03808 -0.1090 0.8330 0.0059
-10.250 -0.4846 0.04040 0.03470 -0.1049 0.8294 0.0060
-10.000 -0.4922 0.03817 0.03223 -0.1013 0.8257 0.0061
-9.750 -0.4958 0.03572 0.02940 -0.0976 0.8226 0.0060
-9.500 -0.4971 0.03369 0.02711 -0.0942 0.8199 0.0062
-9.000 -0.4828 0.03027 0.02313 -0.0890 0.8148 0.0065
-8.750 -0.4699 0.02877 0.02138 -0.0872 0.8121 0.0068
-8.500 -0.4505 0.02706 0.01938 -0.0863 0.8100 0.0070
-8.250 -0.4279 0.02556 0.01762 -0.0859 0.8083 0.0072
-8.000 -0.4051 0.02451 0.01633 -0.0855 0.8067 0.0081
-7.750 -0.3826 0.02352 0.01517 -0.0852 0.8052 0.0096
-7.500 -0.3598 0.02267 0.01421 -0.0848 0.8039 0.0102
-7.250 -0.3364 0.02176 0.01319 -0.0845 0.8023 0.0111
-7.000 -0.3146 0.02088 0.01221 -0.0838 0.8005 0.0117
-6.750 -0.2947 0.02010 0.01131 -0.0827 0.7987 0.0129
-6.500 -0.2767 0.01933 0.01049 -0.0815 0.7969 0.0145
-6.250 -0.2568 0.01884 0.00992 -0.0804 0.7953 0.0171
-6.000 -0.2381 0.01825 0.00930 -0.0792 0.7938 0.0235
-5.750 -0.2195 0.01769 0.00874 -0.0779 0.7923 0.0328
-5.500 -0.2010 0.01719 0.00828 -0.0765 0.7909 0.0504
-5.250 -0.1831 0.01672 0.00791 -0.0752 0.7896 0.0780
-5.000 -0.1683 0.01629 0.00768 -0.0733 0.7878 0.1191
-4.750 -0.1558 0.01586 0.00748 -0.0710 0.7860 0.1733
-4.500 -0.1485 0.01537 0.00731 -0.0678 0.7841 0.2491
-4.250 -0.1495 0.01481 0.00718 -0.0627 0.7821 0.3467
-4.000 -0.1563 0.01412 0.00703 -0.0564 0.7801 0.4673
-3.750 -0.0538 0.01537 0.00936 -0.0682 0.7813 0.7457
-3.500 -0.0424 0.01557 0.00948 -0.0650 0.7798 0.7694
-3.250 -0.0461 0.01555 0.00939 -0.0591 0.7781 0.7899
-3.000 -0.0317 0.01595 0.00970 -0.0561 0.7769 0.8044
-2.750 0.0089 0.01667 0.01029 -0.0580 0.7763 0.8141
-2.500 0.0564 0.01761 0.01111 -0.0610 0.7758 0.8268
-2.250 0.0954 0.01821 0.01161 -0.0629 0.7751 0.8357
-2.000 0.1109 0.01852 0.01191 -0.0607 0.7733 0.8439
-1.750 0.1358 0.01872 0.01205 -0.0605 0.7718 0.8477
-1.500 0.1673 0.01888 0.01215 -0.0617 0.7707 0.8497
-1.000 0.1911 0.01913 0.01236 -0.0562 0.7673 0.8607
-0.750 0.2231 0.01921 0.01238 -0.0575 0.7663 0.8620
-0.500 0.2531 0.01925 0.01239 -0.0584 0.7652 0.8635
-0.250 0.2802 0.01930 0.01240 -0.0587 0.7642 0.8656
0.000 0.2687 0.01931 0.01239 -0.0512 0.7626 0.8741
0.250 0.3011 0.01935 0.01241 -0.0526 0.7619 0.8750
0.500 0.3289 0.01948 0.01254 -0.0532 0.7609 0.8762
0.750 0.3396 0.01999 0.01312 -0.0506 0.7574 0.8788
1.000 0.3426 0.02035 0.01350 -0.0462 0.7545 0.8830
1.250 0.3292 0.02044 0.01360 -0.0384 0.7515 0.8894
1.500 0.3568 0.02050 0.01366 -0.0389 0.7503 0.8905
1.750 0.3844 0.02053 0.01371 -0.0393 0.7493 0.8917
2.000 0.4113 0.02051 0.01369 -0.0396 0.7483 0.8929
2.250 0.4374 0.02048 0.01368 -0.0396 0.7475 0.8944
2.750 0.3906 0.02152 0.01482 -0.0209 0.7356 0.9059
3.000 0.3851 0.02190 0.01523 -0.0151 0.7311 0.9095
3.250 0.4383 0.02150 0.01486 -0.0202 0.7328 0.9086
4.250 0.4092 0.02310 0.01660 0.0037 0.7078 0.9246
4.750 0.4217 0.02356 0.01714 0.0102 0.6956 0.9307
5.000 0.4561 0.02310 0.01675 0.0091 0.6941 0.9312
5.250 0.4952 0.02235 0.01609 0.0073 0.6931 0.9314
5.500 0.5305 0.02166 0.01547 0.0062 0.6904 0.9319
6.000 0.5678 0.02125 0.01522 0.0091 0.6756 0.9356
6.500 0.5789 0.02171 0.01584 0.0158 0.6536 0.9422
7.500 0.6295 0.02279 0.01727 0.0231 0.5867 0.9515
7.750 0.7246 0.01797 0.01204 0.0167 0.5029 0.9478
8.000 0.7253 0.01874 0.01228 0.0208 0.4178 0.9511
8.250 0.7151 0.02009 0.01328 0.0258 0.3548 0.9557
8.500 0.7128 0.02148 0.01439 0.0290 0.2988 0.9587
8.750 0.7151 0.02292 0.01557 0.0312 0.2439 0.9613
9.000 0.7203 0.02425 0.01666 0.0330 0.1948 0.9639
9.250 0.7279 0.02547 0.01769 0.0345 0.1526 0.9666
9.500 0.7377 0.02656 0.01864 0.0358 0.1191 0.9694
9.750 0.7515 0.02766 0.01962 0.0363 0.0920 0.9714
10.000 0.7675 0.02876 0.02065 0.0364 0.0716 0.9732
10.250 0.7840 0.02981 0.02170 0.0365 0.0579 0.9753
10.500 0.7999 0.03090 0.02278 0.0366 0.0467 0.9775
10.750 0.8143 0.03207 0.02394 0.0369 0.0393 0.9798
11.000 0.8302 0.03311 0.02513 0.0372 0.0346 0.9824
11.250 0.8434 0.03451 0.02654 0.0374 0.0297 0.9844
11.500 0.8608 0.03559 0.02775 0.0372 0.0263 0.9867
11.750 0.8755 0.03683 0.02907 0.0373 0.0232 0.9897
12.000 0.8868 0.03829 0.03058 0.0377 0.0204 0.9936
12.250 0.9013 0.03973 0.03217 0.0378 0.0186 0.9998
12.500 0.9063 0.04070 0.03321 0.0398 0.0168 1.0000
12.750 0.9103 0.04204 0.03457 0.0415 0.0150 1.0000
13.000 0.9171 0.04344 0.03608 0.0430 0.0138 1.0000
13.250 0.9261 0.04475 0.03754 0.0439 0.0118 1.0000
13.500 0.9340 0.04620 0.03905 0.0447 0.0106 1.0000
13.750 0.9402 0.04797 0.04093 0.0456 0.0093 1.0000
14.000 0.9464 0.04981 0.04292 0.0465 0.0088 1.0000
14.250 0.9522 0.05174 0.04500 0.0473 0.0084 1.0000
14.500 0.9565 0.05386 0.04724 0.0479 0.0075 1.0000
14.750 0.9604 0.05607 0.04957 0.0484 0.0071 1.0000
15.000 0.9577 0.05906 0.05266 0.0491 0.0066 1.0000
15.250 0.9593 0.06174 0.05552 0.0495 0.0065 1.0000
15.500 0.9597 0.06469 0.05876 0.0498 0.0057 1.0000
15.750 0.9580 0.06791 0.06217 0.0499 0.0058 1.0000
16.000 0.9523 0.07177 0.06625 0.0498 0.0057 1.0000
16.250 0.9495 0.07526 0.06993 0.0491 0.0052 1.0000
16.500 0.9405 0.07986 0.07474 0.0483 0.0051 1.0000
16.750 0.9400 0.08322 0.07819 0.0468 0.0047 1.0000
17.000 0.9215 0.08976 0.08503 0.0452 0.0049 1.0000
17.250 0.9235 0.09300 0.08827 0.0430 0.0044 1.0000
17.500 0.9064 0.09984 0.09542 0.0405 0.0046 1.0000
17.750 0.8806 0.10880 0.10465 0.0366 0.0047 1.0000
18.000 0.8810 0.11293 0.10874 0.0334 0.0041 1.0000
18.250 0.8524 0.12355 0.11969 0.0282 0.0046 1.0000
18.500 0.8091 0.13904 0.13552 0.0199 0.0050 1.0000
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