NREL's S806A Airfoil (modified line 35) (s806a-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S806A Airfoil (modified line 35) (s806a-nr) Reynolds number: 100,000 Max Cl/Cd: 53.32 at α=7° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s806a-nr-100000.txt Download as CSV file: xf-s806a-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S806A Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4417 0.12228 0.11769 -0.0361 1.0000 0.0795
-10.000 -0.4457 0.11912 0.11459 -0.0419 1.0000 0.0798
-9.750 -0.4512 0.11566 0.11117 -0.0475 1.0000 0.0800
-2.250 -0.0210 0.02731 0.01716 -0.0672 0.9119 0.0480
-2.000 0.0038 0.02675 0.01658 -0.0670 0.9095 0.0475
-1.750 0.1663 0.02197 0.01523 -0.0848 0.9171 1.0000
-1.500 0.1483 0.02261 0.01582 -0.0776 0.9111 1.0000
-1.250 0.1516 0.02303 0.01612 -0.0742 0.9068 1.0000
-1.000 0.1796 0.02328 0.01618 -0.0750 0.9031 1.0000
-0.750 0.2215 0.02354 0.01626 -0.0783 0.9003 1.0000
-0.500 0.1560 0.02430 0.01706 -0.0625 0.8931 1.0000
-0.250 0.1554 0.02480 0.01747 -0.0585 0.8892 1.0000
0.000 0.1668 0.02531 0.01787 -0.0566 0.8858 1.0000
0.250 0.1841 0.02584 0.01830 -0.0558 0.8815 1.0000
0.500 0.2088 0.02632 0.01868 -0.0560 0.8755 1.0000
0.750 0.2380 0.02681 0.01908 -0.0570 0.8699 1.0000
1.000 0.2674 0.02740 0.01959 -0.0582 0.8660 1.0000
1.250 0.2998 0.02803 0.02017 -0.0599 0.8622 1.0000
1.500 0.3376 0.02870 0.02065 -0.0623 0.8584 1.0000
1.750 0.3835 0.02960 0.02163 -0.0659 0.8538 1.0000
2.000 0.4040 0.03074 0.02275 -0.0654 0.8469 1.0000
2.250 0.4035 0.03101 0.02300 -0.0618 0.8394 1.0000
2.500 0.4159 0.03152 0.02351 -0.0602 0.8312 1.0000
2.750 0.4412 0.03194 0.02393 -0.0603 0.8222 1.0000
3.000 0.4762 0.03230 0.02432 -0.0617 0.8146 1.0000
3.250 0.5198 0.03268 0.02474 -0.0643 0.8086 1.0000
3.500 0.5740 0.03318 0.02532 -0.0683 0.8032 1.0000
3.750 0.5655 0.03405 0.02621 -0.0635 0.7893 1.0000
4.000 0.5772 0.03448 0.02668 -0.0615 0.7763 1.0000
4.250 0.6131 0.03439 0.02669 -0.0623 0.7660 1.0000
4.500 0.6705 0.03364 0.02608 -0.0654 0.7584 1.0000
4.750 0.7308 0.03270 0.02543 -0.0682 0.7519 1.0000
5.000 0.7153 0.03396 0.02673 -0.0635 0.7302 1.0000
5.250 0.7565 0.03280 0.02573 -0.0637 0.7174 1.0000
5.500 0.8126 0.03004 0.02318 -0.0635 0.7080 1.0000
5.750 0.8773 0.01994 0.01297 -0.0554 0.6384 1.0000
6.000 0.8909 0.02759 0.02094 -0.0649 0.6790 1.0000
6.250 0.9310 0.02507 0.01859 -0.0635 0.6639 1.0000
6.500 0.9746 0.02188 0.01552 -0.0616 0.6461 1.0000
6.750 0.9984 0.02048 0.01429 -0.0592 0.6058 1.0000
7.000 1.0232 0.01919 0.01288 -0.0564 0.5235 1.0000
7.250 1.0297 0.01994 0.01222 -0.0513 0.3475 1.0000
7.500 1.0269 0.02224 0.01367 -0.0474 0.2396 1.0000
7.750 1.0248 0.02455 0.01562 -0.0438 0.1643 1.0000
8.000 1.0285 0.02643 0.01714 -0.0410 0.1248 1.0000
8.250 1.0322 0.02813 0.01860 -0.0382 0.1028 1.0000
8.500 1.0414 0.02982 0.02021 -0.0359 0.0871 1.0000
8.750 1.0550 0.03174 0.02204 -0.0340 0.0757 1.0000
9.000 1.0718 0.03322 0.02355 -0.0327 0.0666 1.0000
9.250 1.1022 0.03588 0.02618 -0.0329 0.0580 1.0000
9.500 1.1273 0.03759 0.02801 -0.0326 0.0538 1.0000
9.750 1.1561 0.03980 0.03022 -0.0330 0.0511 1.0000
10.000 1.1914 0.04360 0.03417 -0.0342 0.0497 1.0000
10.250 1.2116 0.04673 0.03768 -0.0334 0.0494 1.0000
10.500 1.2273 0.05025 0.04167 -0.0323 0.0494 1.0000
10.750 1.2404 0.05428 0.04604 -0.0311 0.0497 1.0000
11.000 1.2479 0.05756 0.04971 -0.0292 0.0503 1.0000
11.250 1.2381 0.06048 0.05322 -0.0252 0.0514 1.0000
11.500 1.2068 0.06458 0.05791 -0.0197 0.0529 1.0000
11.750 1.1797 0.06923 0.06296 -0.0163 0.0541 1.0000
12.000 1.1542 0.07413 0.06818 -0.0141 0.0551 1.0000
12.250 1.1288 0.07939 0.07369 -0.0129 0.0561 1.0000
12.500 1.1027 0.08505 0.07957 -0.0126 0.0569 1.0000
12.750 1.0757 0.09134 0.08604 -0.0132 0.0577 1.0000
13.000 1.0484 0.09840 0.09324 -0.0147 0.0586 1.0000
13.250 1.0475 0.10363 0.09859 -0.0153 0.0610 1.0000
13.500 1.0137 0.11095 0.10605 -0.0197 0.0623 1.0000
13.750 0.9348 0.13912 0.13437 -0.0365 0.0821 1.0000
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Polar data table (+)
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