NREL's S805A Airfoil (s805a-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S805A Airfoil (s805a-nr) Reynolds number: 50,000 Max Cl/Cd: 27.11 at α=9° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s805a-nr-50000-n5.txt Download as CSV file: xf-s805a-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S805A Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.050 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.500 -0.4252 0.10158 0.09451 -0.0467 1.0000 0.0557
-10.250 -0.4287 0.09688 0.08987 -0.0486 1.0000 0.0544
-10.000 -0.4358 0.09154 0.08461 -0.0514 1.0000 0.0530
-9.750 -0.4488 0.08556 0.07870 -0.0550 1.0000 0.0516
-9.500 -0.4701 0.08006 0.07324 -0.0576 1.0000 0.0504
-9.250 -0.5001 0.07563 0.06884 -0.0579 1.0000 0.0492
-8.750 -0.5665 0.07014 0.06306 -0.0511 1.0000 0.0472
-8.500 -0.5756 0.06730 0.06018 -0.0484 1.0000 0.0470
-8.250 -0.5852 0.06463 0.05744 -0.0453 1.0000 0.0468
-8.000 -0.5944 0.06216 0.05490 -0.0420 1.0000 0.0465
-7.750 -0.6044 0.05986 0.05249 -0.0383 1.0000 0.0464
-7.500 -0.6142 0.05777 0.05027 -0.0345 1.0000 0.0463
-7.250 -0.6034 0.05424 0.04638 -0.0348 0.9926 0.0461
-7.000 -0.5807 0.05021 0.04181 -0.0368 0.9813 0.0461
-6.750 -0.5555 0.04659 0.03763 -0.0384 0.9707 0.0464
-6.500 -0.5304 0.04342 0.03396 -0.0396 0.9595 0.0479
-6.250 -0.5037 0.04096 0.03130 -0.0408 0.9489 0.0501
-6.000 -0.4732 0.03865 0.02864 -0.0421 0.9397 0.0521
-5.750 -0.4406 0.03633 0.02589 -0.0432 0.9311 0.0536
-5.500 -0.4076 0.03437 0.02359 -0.0441 0.9223 0.0552
-5.250 -0.3679 0.03263 0.02148 -0.0458 0.9161 0.0583
-5.000 -0.3335 0.03120 0.02003 -0.0469 0.9083 0.0635
-4.750 -0.2936 0.02997 0.01858 -0.0485 0.9025 0.0697
-4.500 -0.2630 0.02885 0.01735 -0.0490 0.8945 0.0756
-4.250 -0.2332 0.02776 0.01620 -0.0496 0.8872 0.0888
-4.000 -0.2120 0.02671 0.01521 -0.0489 0.8779 0.1086
-3.750 -0.1924 0.02480 0.01400 -0.0485 0.8710 0.1953
-3.500 -0.1889 0.02363 0.01540 -0.0412 0.8627 0.6628
-3.250 -0.1698 0.02514 0.01672 -0.0356 0.8566 0.7828
-3.000 -0.0667 0.02778 0.01880 -0.0410 0.8594 0.8760
-2.750 -0.0239 0.02756 0.01818 -0.0440 0.8541 0.8885
-2.500 0.0148 0.02734 0.01766 -0.0465 0.8469 0.8972
-2.250 0.0525 0.02703 0.01707 -0.0490 0.8416 0.9044
-2.000 0.0829 0.02690 0.01671 -0.0502 0.8337 0.9120
-1.750 0.1184 0.02666 0.01625 -0.0522 0.8280 0.9189
-1.500 0.1517 0.02654 0.01596 -0.0540 0.8216 0.9269
-1.250 0.1865 0.02640 0.01565 -0.0560 0.8155 0.9342
-1.000 0.2231 0.02618 0.01526 -0.0583 0.8109 0.9402
-0.750 0.2463 0.02628 0.01527 -0.0584 0.8032 0.9464
-0.500 0.2808 0.02614 0.01502 -0.0605 0.7981 0.9508
-0.250 0.3061 0.02623 0.01503 -0.0609 0.7921 0.9565
0.000 0.3353 0.02626 0.01501 -0.0621 0.7860 0.9610
0.250 0.3694 0.02618 0.01485 -0.0640 0.7817 0.9652
0.500 0.3905 0.02647 0.01513 -0.0639 0.7750 0.9708
0.750 0.4222 0.02651 0.01516 -0.0655 0.7698 0.9749
1.000 0.4558 0.02648 0.01510 -0.0673 0.7659 0.9788
1.250 0.4759 0.02693 0.01560 -0.0672 0.7587 0.9843
1.500 0.5074 0.02704 0.01573 -0.0688 0.7539 0.9884
1.750 0.5366 0.02721 0.01593 -0.0699 0.7492 0.9928
2.000 0.5602 0.02767 0.01646 -0.0705 0.7425 0.9980
2.250 0.5852 0.02787 0.01670 -0.0707 0.7378 1.0000
2.750 0.6042 0.02900 0.01796 -0.0660 0.7246 1.0000
3.000 0.6201 0.02935 0.01837 -0.0644 0.7193 1.0000
3.250 0.6202 0.03017 0.01926 -0.0607 0.7111 1.0000
3.500 0.6422 0.03031 0.01947 -0.0598 0.7064 1.0000
3.750 0.6332 0.03134 0.02056 -0.0547 0.6968 1.0000
4.000 0.6552 0.03147 0.02080 -0.0538 0.6918 1.0000
4.250 0.6428 0.03250 0.02188 -0.0481 0.6818 1.0000
4.500 0.6680 0.03250 0.02198 -0.0475 0.6766 1.0000
4.750 0.6522 0.03354 0.02306 -0.0413 0.6658 1.0000
5.000 0.6724 0.03364 0.02326 -0.0399 0.6594 1.0000
5.250 0.6690 0.03433 0.02400 -0.0353 0.6492 1.0000
5.500 0.6696 0.03502 0.02478 -0.0315 0.6389 1.0000
5.750 0.7050 0.03461 0.02453 -0.0318 0.6321 1.0000
6.000 0.7082 0.03530 0.02530 -0.0285 0.6198 1.0000
6.250 0.7218 0.03564 0.02575 -0.0264 0.6080 1.0000
6.500 0.7469 0.03542 0.02573 -0.0254 0.5969 1.0000
6.750 0.7887 0.03428 0.02480 -0.0257 0.5865 1.0000
7.000 0.8074 0.03409 0.02477 -0.0237 0.5719 1.0000
7.250 0.8227 0.03398 0.02482 -0.0214 0.5559 1.0000
7.500 0.8274 0.03434 0.02535 -0.0180 0.5376 1.0000
7.750 0.8391 0.03423 0.02540 -0.0153 0.5186 1.0000
8.000 0.8591 0.03354 0.02489 -0.0130 0.4979 1.0000
8.250 0.8596 0.03421 0.02570 -0.0098 0.4729 1.0000
8.500 0.8690 0.03441 0.02604 -0.0073 0.4434 1.0000
8.750 0.8835 0.03428 0.02597 -0.0051 0.4052 1.0000
9.000 0.9068 0.03345 0.02492 -0.0027 0.3500 1.0000
9.250 0.9143 0.03428 0.02532 -0.0001 0.2974 1.0000
9.500 0.9138 0.03608 0.02682 0.0021 0.2569 1.0000
9.750 0.9124 0.03818 0.02865 0.0039 0.2249 1.0000
10.000 0.9125 0.04034 0.03065 0.0054 0.1984 1.0000
10.250 0.9144 0.04250 0.03267 0.0066 0.1766 1.0000
10.500 0.9181 0.04461 0.03469 0.0077 0.1581 1.0000
10.750 0.9235 0.04666 0.03670 0.0086 0.1426 1.0000
11.000 0.9310 0.04860 0.03863 0.0095 0.1292 1.0000
11.250 0.9420 0.05039 0.04044 0.0104 0.1180 1.0000
11.500 0.9540 0.05215 0.04222 0.0112 0.1082 1.0000
11.750 0.9663 0.05389 0.04398 0.0120 0.0993 1.0000
12.000 0.9853 0.05552 0.04586 0.0128 0.0911 1.0000
12.250 1.0022 0.05722 0.04760 0.0135 0.0840 1.0000
12.500 1.0156 0.05948 0.05018 0.0140 0.0776 1.0000
12.750 1.0315 0.06149 0.05217 0.0146 0.0720 1.0000
13.000 1.0334 0.06472 0.05583 0.0148 0.0677 1.0000
13.250 1.0377 0.06765 0.05895 0.0150 0.0638 1.0000
13.500 1.0441 0.07045 0.06177 0.0152 0.0601 1.0000
13.750 1.0338 0.07493 0.06667 0.0147 0.0580 1.0000
14.000 1.0225 0.07964 0.07171 0.0138 0.0561 1.0000
14.250 1.0098 0.08464 0.07698 0.0125 0.0546 1.0000
14.500 0.9955 0.09009 0.08267 0.0107 0.0535 1.0000
14.750 0.9780 0.09627 0.08907 0.0082 0.0529 1.0000
15.000 0.9526 0.10428 0.09731 0.0042 0.0532 1.0000
15.250 0.9156 0.11557 0.10882 -0.0023 0.0548 1.0000
15.500 0.8788 0.12888 0.12224 -0.0104 0.0568 1.0000
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