NREL's S823 Airfoil (s823-nr) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: NREL's S823 Airfoil (s823-nr) Reynolds number: 200,000 Max Cl/Cd: 62.49 at α=8° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s823-nr-200000.txt Download as CSV file: xf-s823-nr-200000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S823 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.8014 0.04573 0.03955 -0.0663 0.9923 0.1642
-9.250 -0.8091 0.04034 0.03384 -0.0745 0.9810 0.1651
-9.000 -0.8002 0.03716 0.03042 -0.0796 0.9696 0.1661
-8.750 -0.7813 0.03490 0.02796 -0.0832 0.9601 0.1672
-8.500 -0.7501 0.03299 0.02584 -0.0877 0.9548 0.1683
-8.250 -0.7285 0.03160 0.02427 -0.0894 0.9454 0.1692
-8.000 -0.6952 0.02982 0.02246 -0.0924 0.9415 0.1710
-7.750 -0.6640 0.02888 0.02155 -0.0942 0.9357 0.1726
-7.500 -0.6322 0.02809 0.02076 -0.0960 0.9293 0.1742
-7.250 -0.5928 0.02720 0.01987 -0.0992 0.9261 0.1763
-7.000 -0.5575 0.02632 0.01893 -0.1017 0.9216 0.1784
-6.750 -0.5288 0.02546 0.01798 -0.1031 0.9140 0.1807
-6.500 -0.4884 0.02448 0.01683 -0.1067 0.9109 0.1832
-6.250 -0.4451 0.02335 0.01574 -0.1103 0.9089 0.1863
-6.000 -0.4164 0.02281 0.01526 -0.1110 0.9007 0.1888
-5.750 -0.3767 0.02218 0.01465 -0.1138 0.8961 0.1923
-5.500 -0.3331 0.02147 0.01384 -0.1175 0.8927 0.1966
-5.250 -0.3055 0.02087 0.01318 -0.1181 0.8835 0.2003
-5.000 -0.2666 0.02031 0.01273 -0.1205 0.8781 0.2046
-4.750 -0.2333 0.01994 0.01235 -0.1219 0.8706 0.2092
-4.500 -0.2006 0.01952 0.01176 -0.1234 0.8624 0.2141
-4.250 -0.1682 0.01901 0.01138 -0.1244 0.8549 0.2187
-4.000 -0.1383 0.01875 0.01112 -0.1251 0.8457 0.2235
-3.750 -0.1072 0.01847 0.01071 -0.1260 0.8376 0.2290
-3.500 -0.0786 0.01811 0.01044 -0.1263 0.8287 0.2338
-3.250 -0.0492 0.01795 0.01028 -0.1267 0.8202 0.2389
-3.000 -0.0195 0.01775 0.00995 -0.1272 0.8113 0.2448
-2.750 0.0082 0.01750 0.00980 -0.1273 0.8029 0.2497
-2.500 0.0375 0.01737 0.00968 -0.1276 0.7944 0.2552
-2.250 0.0661 0.01726 0.00943 -0.1279 0.7859 0.2612
-2.000 0.0945 0.01705 0.00933 -0.1280 0.7775 0.2663
-1.750 0.1227 0.01700 0.00928 -0.1281 0.7694 0.2724
-1.500 0.1516 0.01686 0.00908 -0.1283 0.7611 0.2788
-1.250 0.1799 0.01680 0.00911 -0.1283 0.7533 0.2844
-1.000 0.2083 0.01676 0.00902 -0.1284 0.7450 0.2913
-0.750 0.2376 0.01666 0.00894 -0.1286 0.7378 0.2973
-0.500 0.2645 0.01664 0.00898 -0.1284 0.7292 0.3035
-0.250 0.2960 0.01658 0.00882 -0.1290 0.7227 0.3108
0.000 0.3212 0.01657 0.00895 -0.1284 0.7140 0.3167
0.250 0.3530 0.01659 0.00887 -0.1290 0.7075 0.3250
0.500 0.3781 0.01657 0.00899 -0.1284 0.6991 0.3312
0.750 0.4083 0.01658 0.00899 -0.1287 0.6923 0.3389
1.000 0.4356 0.01657 0.00902 -0.1285 0.6848 0.3458
1.250 0.4640 0.01659 0.00910 -0.1284 0.6775 0.3528
1.500 0.4941 0.01660 0.00905 -0.1287 0.6711 0.3606
1.750 0.5200 0.01661 0.00921 -0.1282 0.6631 0.3667
2.000 0.5520 0.01666 0.00914 -0.1287 0.6571 0.3754
2.250 0.5767 0.01668 0.00935 -0.1280 0.6494 0.3817
2.500 0.6065 0.01673 0.00938 -0.1281 0.6427 0.3902
2.750 0.6342 0.01677 0.00950 -0.1279 0.6360 0.3971
3.000 0.6614 0.01683 0.00962 -0.1276 0.6285 0.4050
3.250 0.6929 0.01687 0.00964 -0.1280 0.6224 0.4131
3.500 0.7168 0.01696 0.00986 -0.1270 0.6139 0.4211
3.750 0.7474 0.01697 0.00985 -0.1272 0.6070 0.4294
4.000 0.7716 0.01705 0.01005 -0.1263 0.5982 0.4375
4.250 0.8014 0.01706 0.01006 -0.1263 0.5907 0.4462
4.500 0.8258 0.01715 0.01026 -0.1254 0.5819 0.4547
4.750 0.8549 0.01717 0.01027 -0.1253 0.5739 0.4634
5.000 0.8788 0.01725 0.01047 -0.1242 0.5646 0.4723
5.250 0.9079 0.01728 0.01048 -0.1241 0.5562 0.4812
5.500 0.9305 0.01736 0.01068 -0.1228 0.5461 0.4904
5.750 0.9577 0.01741 0.01075 -0.1223 0.5373 0.4992
6.000 0.9810 0.01748 0.01088 -0.1211 0.5267 0.5094
6.250 1.0044 0.01754 0.01106 -0.1200 0.5165 0.5177
6.500 1.0306 0.01761 0.01108 -0.1193 0.5060 0.5283
6.750 1.0499 0.01767 0.01132 -0.1174 0.4939 0.5370
7.000 1.0717 0.01777 0.01147 -0.1159 0.4818 0.5471
7.250 1.0928 0.01788 0.01162 -0.1143 0.4692 0.5571
7.500 1.1127 0.01800 0.01176 -0.1126 0.4557 0.5668
7.750 1.1302 0.01816 0.01197 -0.1104 0.4406 0.5780
8.000 1.1454 0.01833 0.01224 -0.1079 0.4246 0.5870
8.250 1.1595 0.01857 0.01250 -0.1052 0.4074 0.5977
8.500 1.1690 0.01884 0.01279 -0.1018 0.3891 0.6079
8.750 1.1775 0.01921 0.01319 -0.0983 0.3685 0.6179
9.000 1.1851 0.01976 0.01370 -0.0949 0.3459 0.6294
9.250 1.1900 0.02044 0.01434 -0.0912 0.3225 0.6395
9.500 1.1939 0.02126 0.01511 -0.0876 0.2975 0.6506
9.750 1.1961 0.02227 0.01604 -0.0841 0.2731 0.6628
10.000 1.1969 0.02341 0.01714 -0.0806 0.2493 0.6740
10.250 1.1960 0.02475 0.01841 -0.0772 0.2282 0.6859
10.500 1.1973 0.02613 0.01977 -0.0744 0.2078 0.6992
10.750 1.1978 0.02767 0.02127 -0.0717 0.1894 0.7136
11.000 1.1983 0.02931 0.02290 -0.0693 0.1728 0.7287
11.250 1.1987 0.03103 0.02463 -0.0670 0.1581 0.7447
11.500 1.1991 0.03284 0.02646 -0.0649 0.1448 0.7625
11.750 1.1987 0.03478 0.02842 -0.0630 0.1331 0.7822
12.000 1.1975 0.03681 0.03049 -0.0611 0.1226 0.8063
12.250 1.1980 0.03857 0.03236 -0.0591 0.1129 0.8402
12.500 1.1862 0.04023 0.03415 -0.0555 0.1068 1.0000
12.750 1.1929 0.04252 0.03644 -0.0555 0.0975 1.0000
13.000 1.1961 0.04507 0.03894 -0.0552 0.0900 1.0000
13.250 1.1977 0.04778 0.04160 -0.0550 0.0833 1.0000
13.500 1.2012 0.05037 0.04420 -0.0547 0.0770 1.0000
13.750 1.2023 0.05324 0.04703 -0.0546 0.0716 1.0000
14.000 1.2048 0.05605 0.04985 -0.0545 0.0665 1.0000
14.250 1.2076 0.05888 0.05270 -0.0546 0.0621 1.0000
14.500 1.2068 0.06212 0.05589 -0.0546 0.0582 1.0000
14.750 1.2113 0.06494 0.05879 -0.0549 0.0543 1.0000
15.000 1.2122 0.06816 0.06199 -0.0552 0.0512 1.0000
15.250 1.2142 0.07129 0.06514 -0.0555 0.0481 1.0000
15.500 1.2174 0.07441 0.06834 -0.0560 0.0452 1.0000
15.750 1.2189 0.07771 0.07163 -0.0566 0.0430 1.0000
16.000 1.2214 0.08089 0.07482 -0.0569 0.0407 1.0000
16.250 1.2245 0.08418 0.07821 -0.0577 0.0386 1.0000
16.500 1.2272 0.08749 0.08154 -0.0585 0.0368 1.0000
16.750 1.2305 0.09058 0.08457 -0.0590 0.0352 1.0000
17.000 1.2340 0.09385 0.08794 -0.0597 0.0337 1.0000
17.250 1.2370 0.09726 0.09146 -0.0606 0.0324 1.0000
17.500 1.2400 0.10065 0.09491 -0.0617 0.0311 1.0000
17.750 1.2439 0.10382 0.09807 -0.0626 0.0301 1.0000
18.000 1.2526 0.10602 0.10019 -0.0627 0.0289 1.0000
18.250 1.2518 0.11020 0.10456 -0.0644 0.0281 1.0000
18.500 1.2522 0.11417 0.10867 -0.0660 0.0272 1.0000
|
Polar data table (+)
Polar graphs
<< Back to NREL's S823 Airfoil (s823-nr)