NREL's S828 Airfoil (s828-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S828 Airfoil (s828-nr) Reynolds number: 200,000 Max Cl/Cd: 63.86 at α=6.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s828-nr-200000.txt Download as CSV file: xf-s828-nr-200000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-12.250 -0.2203 0.10379 0.10017 -0.1107 0.9418 0.0419
-12.000 -0.2203 0.09963 0.09601 -0.1130 0.9357 0.0430
-11.750 -0.2308 0.09339 0.08978 -0.1183 0.9304 0.0459
-11.500 -0.1868 0.08179 0.07834 -0.1143 0.9032 0.0485
-11.250 -0.1795 0.07929 0.07583 -0.1136 0.9004 0.0499
-11.000 -0.1835 0.07482 0.07137 -0.1153 0.8976 0.0507
-10.750 -0.2003 0.06786 0.06442 -0.1199 0.8950 0.0504
-10.500 -0.2270 0.06114 0.05763 -0.1239 0.8924 0.0501
-10.250 -0.2513 0.05631 0.05271 -0.1247 0.8899 0.0503
-10.000 -0.2697 0.05271 0.04902 -0.1241 0.8872 0.0508
-9.750 -0.2900 0.04937 0.04558 -0.1229 0.8836 0.0508
-9.500 -0.3055 0.04654 0.04266 -0.1206 0.8802 0.0517
-9.250 -0.3201 0.04413 0.04013 -0.1176 0.8772 0.0522
-9.000 -0.3367 0.04182 0.03769 -0.1134 0.8745 0.0530
-8.750 -0.3519 0.03995 0.03570 -0.1091 0.8707 0.0539
-8.500 -0.3625 0.03786 0.03345 -0.1050 0.8669 0.0550
-8.250 -0.4281 0.04166 0.03589 -0.0954 0.8668 0.0281
-8.000 -0.4236 0.03759 0.03138 -0.0913 0.8642 0.0220
-7.750 -0.4194 0.03328 0.02617 -0.0862 0.8622 0.0193
-7.500 -0.4012 0.03155 0.02409 -0.0846 0.8608 0.0190
-7.250 -0.3760 0.02920 0.02151 -0.0847 0.8598 0.0198
-7.000 -0.3738 0.02971 0.02210 -0.0813 0.8562 0.0222
-6.750 -0.3599 0.02915 0.02135 -0.0791 0.8537 0.0243
-6.500 -0.3249 0.02735 0.01931 -0.0805 0.8528 0.0249
-6.250 -0.2620 0.02445 0.01625 -0.0872 0.8533 0.0272
-6.000 -0.2430 0.02368 0.01551 -0.0860 0.8516 0.0321
-5.750 -0.2290 0.02305 0.01486 -0.0838 0.8497 0.0389
-5.500 -0.2193 0.02250 0.01434 -0.0807 0.8481 0.0519
-5.250 -0.2115 0.02200 0.01396 -0.0774 0.8468 0.0803
-5.000 -0.2960 0.02587 0.01763 -0.0574 0.8393 0.0451
-4.750 -0.3338 0.02700 0.01873 -0.0457 0.8365 0.0426
-4.500 -0.3422 0.02706 0.01875 -0.0392 0.8352 0.0492
-4.250 -0.3352 0.02647 0.01831 -0.0356 0.8339 0.0770
-4.000 -0.3354 0.02599 0.01817 -0.0309 0.8330 0.1341
-3.750 -0.3425 0.02559 0.01829 -0.0252 0.8325 0.2282
-3.500 -0.3595 0.02510 0.01844 -0.0177 0.8310 0.3580
-3.250 -0.3826 0.02460 0.01866 -0.0090 0.8308 0.5013
-3.000 -0.3862 0.02558 0.02099 -0.0007 0.8299 0.7969
-2.750 -0.0689 0.03046 0.02505 -0.0479 0.8321 0.8669
-2.500 0.0587 0.03108 0.02540 -0.0660 0.8332 0.8816
-2.250 0.1291 0.03133 0.02552 -0.0741 0.8335 0.8945
-2.000 -0.0738 0.03391 0.02842 -0.0333 0.8259 0.9046
-1.750 0.1674 0.03249 0.02656 -0.0721 0.8309 0.9166
-1.500 0.2335 0.03186 0.02583 -0.0801 0.8313 0.9195
-0.250 0.2636 0.03509 0.02900 -0.0655 0.8187 0.9600
0.000 0.2514 0.03607 0.03000 -0.0598 0.8146 0.9667
0.250 0.2526 0.03667 0.03060 -0.0565 0.8111 0.9724
0.500 0.2832 0.03675 0.03066 -0.0582 0.8086 0.9757
0.750 0.3154 0.03679 0.03069 -0.0599 0.8067 0.9789
1.000 0.3503 0.03681 0.03069 -0.0619 0.8051 0.9815
1.250 0.3976 0.03660 0.03049 -0.0662 0.8040 0.9840
1.500 0.3716 0.03762 0.03154 -0.0585 0.7952 0.9875
1.750 0.4066 0.03757 0.03149 -0.0606 0.7927 0.9895
2.000 0.4462 0.03745 0.03138 -0.0633 0.7910 0.9911
2.250 0.4905 0.03727 0.03124 -0.0668 0.7898 0.9924
2.500 0.4682 0.03815 0.03216 -0.0593 0.7792 0.9946
2.750 0.5099 0.03792 0.03196 -0.0624 0.7773 0.9957
3.000 0.5569 0.03762 0.03171 -0.0663 0.7760 0.9969
3.250 0.5421 0.03833 0.03246 -0.0599 0.7651 0.9980
3.500 0.5866 0.03792 0.03212 -0.0631 0.7631 0.9989
3.750 0.6299 0.03756 0.03184 -0.0662 0.7606 1.0000
4.000 0.6240 0.03792 0.03224 -0.0609 0.7503 1.0000
4.250 0.6739 0.03698 0.03141 -0.0643 0.7485 1.0000
4.500 0.7456 0.03509 0.02965 -0.0710 0.7474 1.0000
4.750 0.8961 0.02927 0.02409 -0.0897 0.7468 1.0000
5.000 0.7432 0.03510 0.02978 -0.0610 0.7248 1.0000
5.250 0.8404 0.03136 0.02624 -0.0706 0.7233 1.0000
5.500 1.0805 0.02017 0.01538 -0.1025 0.7211 1.0000
5.750 1.1109 0.01859 0.01388 -0.1018 0.7062 1.0000
6.000 1.1183 0.01812 0.01356 -0.0975 0.6884 1.0000
6.250 1.1172 0.01799 0.01355 -0.0917 0.6670 1.0000
6.750 1.1042 0.01729 0.01208 -0.0767 0.4978 1.0000
7.000 1.0721 0.01812 0.01267 -0.0655 0.4587 1.0000
7.250 1.0404 0.01927 0.01357 -0.0551 0.4171 1.0000
7.500 1.0106 0.02062 0.01467 -0.0456 0.3735 1.0000
7.750 0.9853 0.02203 0.01584 -0.0373 0.3306 1.0000
8.000 0.9622 0.02352 0.01707 -0.0298 0.2851 1.0000
8.250 0.9426 0.02502 0.01829 -0.0230 0.2378 1.0000
8.500 0.9273 0.02644 0.01944 -0.0171 0.1919 1.0000
8.750 0.9146 0.02784 0.02057 -0.0117 0.1491 1.0000
9.000 0.9045 0.02919 0.02167 -0.0067 0.1159 1.0000
9.250 0.8982 0.03040 0.02273 -0.0022 0.0925 1.0000
9.500 0.8935 0.03157 0.02379 0.0020 0.0777 1.0000
9.750 0.8919 0.03257 0.02478 0.0058 0.0672 1.0000
10.000 0.8889 0.03371 0.02591 0.0098 0.0598 1.0000
10.250 0.8897 0.03459 0.02680 0.0132 0.0538 1.0000
10.500 0.8895 0.03563 0.02787 0.0168 0.0488 1.0000
10.750 0.8927 0.03638 0.02869 0.0200 0.0447 1.0000
11.000 0.8947 0.03730 0.02959 0.0232 0.0413 1.0000
11.250 0.8997 0.03814 0.03050 0.0262 0.0373 1.0000
11.500 0.9050 0.03886 0.03131 0.0292 0.0343 1.0000
11.750 0.9082 0.03973 0.03215 0.0323 0.0310 1.0000
12.000 0.9192 0.04075 0.03329 0.0348 0.0276 1.0000
12.250 0.9276 0.04161 0.03428 0.0374 0.0255 1.0000
12.500 0.9284 0.04249 0.03520 0.0405 0.0233 1.0000
12.750 0.9438 0.04448 0.03733 0.0419 0.0205 1.0000
13.000 0.9478 0.04577 0.03881 0.0442 0.0191 1.0000
13.250 0.9531 0.04758 0.04083 0.0460 0.0170 1.0000
13.500 0.9599 0.04961 0.04302 0.0473 0.0162 1.0000
13.750 0.9667 0.05251 0.04606 0.0485 0.0153 1.0000
14.000 0.9631 0.05724 0.05114 0.0501 0.0148 1.0000
14.250 0.9627 0.05932 0.05341 0.0514 0.0150 1.0000
14.500 0.9428 0.06480 0.05924 0.0533 0.0147 1.0000
14.750 0.9300 0.06736 0.06204 0.0544 0.0145 1.0000
15.000 0.9134 0.07108 0.06605 0.0552 0.0140 1.0000
16.250 0.8212 0.09900 0.09497 0.0495 0.0144 1.0000
16.500 0.6293 0.10340 0.10017 0.0481 0.0185 1.0000
16.750 0.5992 0.11111 0.10802 0.0429 0.0192 1.0000
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