NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 100,000 Max Cl/Cd: 35.16 at α=9.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s813-nr-100000.txt Download as CSV file: xf-s813-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S813 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
------ -------- --------- --------- -------- -------- --------
-11.000 -0.3860 0.07811 0.07398 -0.0845 0.9723 0.0746
-10.750 -0.4080 0.10816 0.10387 -0.0590 0.9849 0.1562
-10.500 -0.5093 0.08441 0.08016 -0.0824 0.9763 0.1075
-10.250 -0.5691 0.06932 0.06472 -0.0897 0.9701 0.0745
-10.000 -0.6131 0.06594 0.06108 -0.0874 0.9604 0.0722
-9.750 -0.6520 0.06278 0.05743 -0.0830 0.9515 0.0669
-9.500 -0.6540 0.05888 0.05336 -0.0819 0.9466 0.0648
-9.250 -0.6572 0.05452 0.04860 -0.0809 0.9429 0.0622
-9.000 -0.6789 0.05260 0.04641 -0.0748 0.9370 0.0609
-8.750 -0.6935 0.04924 0.04236 -0.0701 0.9325 0.0584
-8.500 -0.6835 0.04646 0.03898 -0.0685 0.9294 0.0572
-8.250 -0.6739 0.04408 0.03626 -0.0665 0.9264 0.0574
-8.000 -0.6726 0.04254 0.03464 -0.0631 0.9232 0.0591
-7.750 -0.6624 0.04126 0.03325 -0.0610 0.9208 0.0613
-7.500 -0.6479 0.03968 0.03137 -0.0594 0.9185 0.0631
-7.250 -0.6254 0.03787 0.02924 -0.0588 0.9164 0.0645
-7.000 -0.5966 0.03632 0.02739 -0.0590 0.9145 0.0668
-6.750 -0.5693 0.03477 0.02579 -0.0594 0.9128 0.0715
-6.500 -0.5644 0.03421 0.02523 -0.0559 0.9109 0.0745
-6.250 -0.5536 0.03353 0.02448 -0.0533 0.9094 0.0783
-6.000 -0.5408 0.03278 0.02365 -0.0509 0.9075 0.0823
-5.750 -0.5286 0.03195 0.02295 -0.0488 0.9055 0.0899
-5.500 -0.5166 0.03117 0.02226 -0.0468 0.9040 0.1023
-5.250 -0.5074 0.03016 0.02144 -0.0443 0.9032 0.1267
-5.000 -0.5056 0.02803 0.02038 -0.0413 0.9027 0.2548
-4.750 -0.4984 0.02667 0.02014 -0.0389 0.9015 0.4377
-4.500 -0.4852 0.02697 0.02111 -0.0354 0.9002 0.5661
-4.250 -0.6408 0.02791 0.01902 -0.0050 1.0000 0.1142
-4.000 -0.6255 0.02527 0.01778 -0.0043 1.0000 0.2814
-3.750 -0.6148 0.02410 0.01820 -0.0017 1.0000 0.5299
-3.500 -0.6015 0.02479 0.01916 0.0018 1.0000 0.6317
-3.250 -0.5871 0.02570 0.01998 0.0049 1.0000 0.6847
-3.000 -0.5760 0.02676 0.02101 0.0091 1.0000 0.7221
-2.750 -0.5654 0.02765 0.02185 0.0134 1.0000 0.7506
-2.500 -0.5566 0.02840 0.02256 0.0182 1.0000 0.7724
-2.250 -0.5452 0.02891 0.02296 0.0218 1.0000 0.7935
-2.000 -0.5350 0.02930 0.02326 0.0256 1.0000 0.8115
-1.750 -0.5206 0.02986 0.02371 0.0286 0.9980 0.8288
-1.500 -0.5011 0.03069 0.02444 0.0305 0.9944 0.8468
-1.250 -0.4852 0.03107 0.02471 0.0328 0.9907 0.8636
-1.000 -0.4631 0.03178 0.02530 0.0338 0.9853 0.8801
-0.750 -0.4429 0.03242 0.02582 0.0349 0.9821 0.8953
-0.500 -0.4213 0.03262 0.02592 0.0356 0.9754 0.9090
-0.250 -0.3879 0.03380 0.02698 0.0338 0.9712 0.9223
0.000 -0.3627 0.03393 0.02700 0.0333 0.9663 0.9333
0.250 -0.3247 0.03483 0.02779 0.0300 0.9602 0.9435
0.500 -0.2734 0.03671 0.02955 0.0239 0.9571 0.9505
0.750 -0.2445 0.03661 0.02937 0.0220 0.9498 0.9577
1.000 -0.1931 0.03807 0.03074 0.0156 0.9447 0.9625
1.250 -0.1551 0.03911 0.03170 0.0117 0.9407 0.9682
1.500 -0.1128 0.03986 0.03239 0.0070 0.9318 0.9720
1.750 -0.0587 0.04204 0.03451 0.0000 0.9279 0.9757
2.000 -0.0326 0.04184 0.03430 -0.0017 0.9175 0.9806
2.250 0.0182 0.04391 0.03633 -0.0080 0.9130 0.9846
2.500 0.0464 0.04391 0.03634 -0.0102 0.9017 0.9889
2.750 0.0792 0.04484 0.03727 -0.0133 0.8933 0.9940
3.000 0.1268 0.04635 0.03878 -0.0188 0.8848 0.9988
3.250 0.1368 0.04635 0.03878 -0.0174 0.8725 1.0000
3.500 0.1436 0.04646 0.03889 -0.0153 0.8607 1.0000
3.750 0.1706 0.04767 0.04010 -0.0165 0.8530 1.0000
4.000 0.1901 0.04802 0.04046 -0.0162 0.8389 1.0000
4.250 0.2053 0.04814 0.04058 -0.0152 0.8242 1.0000
4.500 0.2300 0.04858 0.04104 -0.0156 0.8077 1.0000
4.750 0.3085 0.04648 0.03895 -0.0193 0.7518 1.0000
5.000 0.3315 0.04668 0.03917 -0.0193 0.7386 1.0000
5.250 0.3597 0.04696 0.03949 -0.0200 0.7261 1.0000
5.500 0.4130 0.04712 0.03975 -0.0234 0.7188 1.0000
5.750 0.4324 0.04737 0.04005 -0.0232 0.7056 1.0000
6.000 0.4565 0.04767 0.04042 -0.0235 0.6929 1.0000
6.250 0.4853 0.04787 0.04071 -0.0242 0.6808 1.0000
6.500 0.5416 0.04722 0.04020 -0.0272 0.6746 1.0000
6.750 0.5674 0.04715 0.04023 -0.0273 0.6614 1.0000
7.000 0.5980 0.04679 0.04000 -0.0276 0.6484 1.0000
7.250 0.6321 0.04611 0.03945 -0.0279 0.6358 1.0000
7.500 0.7014 0.04326 0.03683 -0.0305 0.6309 1.0000
7.750 0.7367 0.04176 0.03551 -0.0303 0.6176 1.0000
8.000 0.7759 0.03973 0.03366 -0.0300 0.6042 1.0000
8.250 0.8169 0.03722 0.03137 -0.0295 0.5904 1.0000
8.500 0.8581 0.03431 0.02870 -0.0286 0.5753 1.0000
8.750 0.8753 0.03332 0.02786 -0.0264 0.5511 1.0000
9.000 0.9041 0.03137 0.02605 -0.0246 0.5170 1.0000
9.250 0.9557 0.02718 0.02110 -0.0222 0.3826 1.0000
9.500 0.9457 0.02923 0.02230 -0.0180 0.2842 1.0000
9.750 0.9368 0.03165 0.02406 -0.0147 0.2188 1.0000
10.000 0.9365 0.03374 0.02565 -0.0122 0.1751 1.0000
10.250 0.9443 0.03546 0.02706 -0.0105 0.1468 1.0000
10.500 0.9589 0.03689 0.02832 -0.0092 0.1271 1.0000
10.750 0.9773 0.03824 0.02953 -0.0083 0.1117 1.0000
11.000 1.0010 0.03954 0.03077 -0.0078 0.0993 1.0000
11.250 1.0283 0.04097 0.03222 -0.0076 0.0884 1.0000
11.500 1.0560 0.04262 0.03383 -0.0077 0.0785 1.0000
11.750 1.0902 0.04467 0.03578 -0.0084 0.0687 1.0000
12.000 1.1008 0.04653 0.03798 -0.0070 0.0632 1.0000
12.250 1.1312 0.04925 0.04066 -0.0076 0.0566 1.0000
12.500 1.1366 0.05157 0.04341 -0.0059 0.0536 1.0000
12.750 1.1494 0.05445 0.04658 -0.0048 0.0509 1.0000
13.000 1.1611 0.05729 0.04958 -0.0040 0.0487 1.0000
13.250 1.1795 0.06258 0.05501 -0.0043 0.0466 1.0000
13.500 1.1634 0.06533 0.05813 -0.0016 0.0461 1.0000
13.750 1.1476 0.06859 0.06174 0.0005 0.0456 1.0000
14.000 1.1310 0.07239 0.06586 0.0021 0.0453 1.0000
14.250 1.1139 0.07672 0.07049 0.0032 0.0452 1.0000
14.500 1.0935 0.08121 0.07526 0.0039 0.0450 1.0000
14.750 1.0722 0.08629 0.08060 0.0040 0.0451 1.0000
15.000 1.0495 0.09169 0.08623 0.0034 0.0452 1.0000
15.250 1.0253 0.09772 0.09248 0.0021 0.0455 1.0000
15.500 1.0044 0.10404 0.09897 0.0002 0.0459 1.0000
15.750 0.9826 0.11090 0.10597 -0.0025 0.0462 1.0000
16.000 0.9655 0.11816 0.11334 -0.0055 0.0466 1.0000
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