NREL's S803 Airfoil (s803-nr) Xfoil prediction polar at RE=50,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S803 Airfoil (s803-nr) Reynolds number: 50,000 Max Cl/Cd: 37.14 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s803-nr-50000-n5.txt Download as CSV file: xf-s803-nr-50000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S803 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3604 0.09933 0.09241 -0.0455 1.0000 0.0601
-8.500 -0.3639 0.09627 0.08944 -0.0451 1.0000 0.0588
-8.250 -0.3705 0.09324 0.08652 -0.0447 1.0000 0.0576
-8.000 -0.3814 0.09020 0.08361 -0.0442 1.0000 0.0566
-7.750 -0.3964 0.08734 0.08090 -0.0432 1.0000 0.0555
-7.500 -0.4156 0.08423 0.07794 -0.0426 1.0000 0.0545
-7.000 -0.4628 0.07206 0.06574 -0.0512 1.0000 0.0506
-6.750 -0.4676 0.06878 0.06243 -0.0513 1.0000 0.0503
-6.500 -0.4518 0.06294 0.05631 -0.0578 0.9939 0.0502
-6.000 -0.3998 0.05272 0.04543 -0.0699 0.9779 0.0526
-5.750 -0.3687 0.04834 0.04062 -0.0750 0.9709 0.0536
-5.500 -0.3360 0.04397 0.03565 -0.0795 0.9636 0.0539
-5.250 -0.3018 0.04044 0.03156 -0.0831 0.9569 0.0547
-5.000 -0.2663 0.03758 0.02819 -0.0862 0.9505 0.0562
-4.750 -0.2319 0.03536 0.02547 -0.0885 0.9437 0.0598
-4.500 -0.1959 0.03338 0.02291 -0.0904 0.9372 0.0628
-4.250 -0.1640 0.03171 0.02114 -0.0916 0.9307 0.0656
-4.000 -0.1324 0.03045 0.01972 -0.0924 0.9237 0.0692
-3.750 -0.0991 0.02940 0.01841 -0.0932 0.9177 0.0762
-3.500 -0.0701 0.02847 0.01747 -0.0937 0.9099 0.0850
-3.250 -0.0337 0.02740 0.01634 -0.0955 0.9051 0.0993
-3.000 -0.0060 0.02650 0.01554 -0.0961 0.8964 0.1277
-2.750 0.0345 0.02482 0.01462 -0.1001 0.8919 0.2462
-2.500 0.0574 0.02366 0.01492 -0.0993 0.8846 0.4984
-2.250 0.0801 0.02401 0.01539 -0.0968 0.8776 0.6495
-2.000 0.0979 0.02439 0.01567 -0.0937 0.8692 0.7111
-1.750 0.1186 0.02458 0.01571 -0.0909 0.8625 0.7560
-1.500 0.1337 0.02471 0.01573 -0.0875 0.8544 0.7895
-1.250 0.1529 0.02468 0.01557 -0.0849 0.8478 0.8211
-1.000 0.1699 0.02465 0.01541 -0.0822 0.8406 0.8494
-0.750 0.1885 0.02453 0.01517 -0.0799 0.8335 0.8773
-0.500 0.2161 0.02426 0.01477 -0.0791 0.8291 0.9061
-0.250 0.2374 0.02431 0.01473 -0.0782 0.8205 0.9339
0.000 0.2843 0.02420 0.01446 -0.0820 0.8166 0.9600
0.250 0.3223 0.02431 0.01444 -0.0849 0.8098 1.0000
0.500 0.3527 0.02455 0.01454 -0.0864 0.8033 1.0000
0.750 0.3924 0.02466 0.01450 -0.0892 0.7995 1.0000
1.000 0.4140 0.02521 0.01496 -0.0894 0.7908 1.0000
1.250 0.4511 0.02541 0.01507 -0.0917 0.7861 1.0000
1.500 0.4806 0.02585 0.01543 -0.0930 0.7797 1.0000
1.750 0.5106 0.02627 0.01580 -0.0943 0.7731 1.0000
2.000 0.5496 0.02643 0.01591 -0.0966 0.7691 1.0000
2.250 0.5710 0.02716 0.01662 -0.0967 0.7603 1.0000
2.500 0.6070 0.02740 0.01683 -0.0985 0.7553 1.0000
2.750 0.6327 0.02800 0.01743 -0.0990 0.7478 1.0000
3.000 0.6642 0.02837 0.01783 -0.1001 0.7413 1.0000
3.250 0.6971 0.02869 0.01816 -0.1013 0.7354 1.0000
3.500 0.7215 0.02930 0.01881 -0.1014 0.7267 1.0000
3.750 0.7625 0.02925 0.01883 -0.1034 0.7223 1.0000
4.000 0.7794 0.03011 0.01975 -0.1024 0.7113 1.0000
4.250 0.8106 0.03038 0.02009 -0.1030 0.7037 1.0000
4.500 0.8395 0.03067 0.02047 -0.1033 0.6946 1.0000
4.750 0.8633 0.03115 0.02107 -0.1028 0.6841 1.0000
5.000 0.9055 0.03071 0.02074 -0.1043 0.6768 1.0000
5.250 0.9270 0.03113 0.02128 -0.1033 0.6639 1.0000
5.500 0.9526 0.03128 0.02159 -0.1026 0.6511 1.0000
5.750 0.9814 0.03118 0.02162 -0.1021 0.6376 1.0000
6.000 1.0105 0.03095 0.02152 -0.1015 0.6229 1.0000
6.250 1.0382 0.03069 0.02144 -0.1005 0.6066 1.0000
6.500 1.0654 0.03036 0.02125 -0.0994 0.5887 1.0000
6.750 1.0946 0.02984 0.02084 -0.0984 0.5692 1.0000
7.000 1.1055 0.03024 0.02140 -0.0955 0.5457 1.0000
7.250 1.1225 0.03026 0.02157 -0.0932 0.5200 1.0000
7.500 1.1336 0.03053 0.02195 -0.0902 0.4903 1.0000
7.750 1.1434 0.03093 0.02242 -0.0871 0.4549 1.0000
8.000 1.1574 0.03116 0.02255 -0.0844 0.4096 1.0000
8.250 1.1694 0.03176 0.02279 -0.0815 0.3585 1.0000
8.500 1.1739 0.03314 0.02387 -0.0785 0.3131 1.0000
8.750 1.1753 0.03495 0.02542 -0.0756 0.2752 1.0000
9.000 1.1766 0.03694 0.02722 -0.0732 0.2448 1.0000
9.250 1.1787 0.03903 0.02917 -0.0710 0.2193 1.0000
9.500 1.1814 0.04118 0.03120 -0.0692 0.1984 1.0000
9.750 1.1860 0.04332 0.03322 -0.0676 0.1812 1.0000
10.000 1.1925 0.04539 0.03528 -0.0662 0.1655 1.0000
10.250 1.2006 0.04742 0.03729 -0.0649 0.1526 1.0000
10.500 1.2111 0.04935 0.03928 -0.0638 0.1406 1.0000
10.750 1.2229 0.05125 0.04127 -0.0627 0.1298 1.0000
11.000 1.2375 0.05304 0.04313 -0.0618 0.1209 1.0000
11.250 1.2530 0.05479 0.04492 -0.0609 0.1127 1.0000
11.500 1.2689 0.05670 0.04707 -0.0601 0.1049 1.0000
11.750 1.2871 0.05844 0.04881 -0.0593 0.0988 1.0000
12.000 1.3030 0.06071 0.05140 -0.0586 0.0931 1.0000
12.250 1.3137 0.06304 0.05389 -0.0578 0.0881 1.0000
12.500 1.3295 0.06533 0.05623 -0.0572 0.0838 1.0000
12.750 1.3342 0.06867 0.06001 -0.0565 0.0806 1.0000
13.000 1.3362 0.07198 0.06361 -0.0559 0.0775 1.0000
13.250 1.3401 0.07491 0.06670 -0.0554 0.0745 1.0000
13.500 1.3445 0.07819 0.07009 -0.0551 0.0720 1.0000
13.750 1.3309 0.08321 0.07554 -0.0552 0.0707 1.0000
14.000 1.3149 0.08872 0.08142 -0.0559 0.0697 1.0000
14.250 1.2956 0.09485 0.08789 -0.0574 0.0690 1.0000
14.500 1.2726 0.10179 0.09514 -0.0598 0.0685 1.0000
14.750 1.2449 0.10994 0.10356 -0.0635 0.0685 1.0000
15.000 1.2118 0.11994 0.11380 -0.0691 0.0689 1.0000
15.250 1.1728 0.13263 0.12663 -0.0772 0.0698 1.0000
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Polar data table (+)
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