NREL's S813 Airfoil (s813-nr) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S813 Airfoil (s813-nr) Reynolds number: 100,000 Max Cl/Cd: 34.43 at α=8.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s813-nr-100000-n5.txt Download as CSV file: xf-s813-nr-100000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-13.000 -0.4653 0.09371 0.08886 -0.0744 1.0000 0.0261
-12.750 -0.4990 0.08371 0.07886 -0.0801 1.0000 0.0256
-12.500 -0.5310 0.07560 0.07069 -0.0851 0.9951 0.0252
-12.250 -0.5527 0.06735 0.06217 -0.0928 0.9802 0.0249
-12.000 -0.5685 0.06107 0.05559 -0.0982 0.9659 0.0248
-11.750 -0.5800 0.05589 0.05008 -0.1019 0.9519 0.0248
-11.500 -0.5873 0.05156 0.04538 -0.1043 0.9384 0.0250
-11.250 -0.5906 0.04791 0.04136 -0.1054 0.9261 0.0251
-11.000 -0.5917 0.04484 0.03790 -0.1054 0.9144 0.0256
-10.750 -0.5905 0.04226 0.03496 -0.1044 0.9036 0.0259
-10.500 -0.5847 0.03994 0.03225 -0.1033 0.8954 0.0264
-10.250 -0.5766 0.03793 0.02988 -0.1018 0.8877 0.0271
-10.000 -0.5644 0.03608 0.02774 -0.1008 0.8821 0.0283
-9.750 -0.5513 0.03477 0.02638 -0.0998 0.8758 0.0297
-9.500 -0.5349 0.03346 0.02491 -0.0990 0.8709 0.0311
-9.250 -0.5146 0.03204 0.02329 -0.0985 0.8666 0.0324
-9.000 -0.4938 0.03072 0.02179 -0.0979 0.8617 0.0337
-8.750 -0.4733 0.02965 0.02050 -0.0972 0.8574 0.0357
-8.500 -0.4564 0.02848 0.01932 -0.0964 0.8539 0.0379
-8.250 -0.4419 0.02769 0.01849 -0.0950 0.8491 0.0403
-8.000 -0.4264 0.02687 0.01755 -0.0937 0.8450 0.0426
-7.750 -0.4106 0.02609 0.01661 -0.0922 0.8415 0.0448
-7.500 -0.3977 0.02518 0.01566 -0.0906 0.8384 0.0486
-7.250 -0.3847 0.02462 0.01503 -0.0889 0.8338 0.0542
-7.000 -0.3721 0.02388 0.01431 -0.0871 0.8298 0.0618
-6.750 -0.3579 0.02310 0.01355 -0.0854 0.8265 0.0757
-6.500 -0.3426 0.02230 0.01287 -0.0839 0.8240 0.1039
-6.250 -0.3312 0.02167 0.01248 -0.0820 0.8203 0.1494
-6.000 -0.3193 0.02106 0.01213 -0.0802 0.8167 0.2038
-5.750 -0.3077 0.02035 0.01178 -0.0782 0.8135 0.2759
-5.500 -0.2972 0.01954 0.01147 -0.0760 0.8107 0.3720
-5.250 -0.2819 0.01903 0.01144 -0.0738 0.8086 0.4675
-5.000 -0.2666 0.01927 0.01198 -0.0712 0.8047 0.5322
-4.750 -0.2460 0.01969 0.01245 -0.0694 0.8018 0.5778
-4.500 -0.2243 0.02004 0.01272 -0.0681 0.7993 0.6101
-4.250 -0.2011 0.02034 0.01288 -0.0671 0.7972 0.6341
-4.000 -0.1766 0.02061 0.01300 -0.0663 0.7952 0.6542
-3.750 -0.1510 0.02086 0.01308 -0.0657 0.7936 0.6711
-3.500 -0.1355 0.02136 0.01352 -0.0635 0.7895 0.6833
-3.250 -0.1161 0.02174 0.01381 -0.0620 0.7865 0.6950
-3.000 -0.0949 0.02200 0.01397 -0.0608 0.7841 0.7066
-2.750 -0.0714 0.02223 0.01408 -0.0600 0.7821 0.7170
-2.500 -0.0457 0.02245 0.01422 -0.0594 0.7804 0.7251
-2.250 -0.0202 0.02251 0.01415 -0.0591 0.7788 0.7353
-2.000 -0.0090 0.02305 0.01470 -0.0563 0.7744 0.7419
-1.750 0.0064 0.02333 0.01491 -0.0547 0.7711 0.7509
-1.500 0.0277 0.02360 0.01513 -0.0535 0.7687 0.7569
-1.250 0.0511 0.02366 0.01510 -0.0531 0.7666 0.7652
-1.000 0.0773 0.02379 0.01518 -0.0527 0.7650 0.7701
-0.750 0.1042 0.02383 0.01515 -0.0528 0.7636 0.7767
-0.500 0.1006 0.02462 0.01598 -0.0483 0.7573 0.7832
-0.250 0.1192 0.02487 0.01620 -0.0470 0.7541 0.7888
0.000 0.1436 0.02495 0.01622 -0.0470 0.7520 0.7952
0.250 0.1690 0.02507 0.01633 -0.0466 0.7504 0.7991
0.500 0.1962 0.02515 0.01638 -0.0468 0.7490 0.8037
1.000 0.2076 0.02635 0.01762 -0.0410 0.7383 0.8145
1.250 0.2338 0.02645 0.01771 -0.0411 0.7363 0.8187
1.500 0.2636 0.02649 0.01773 -0.0418 0.7348 0.8233
1.750 0.2936 0.02652 0.01776 -0.0424 0.7336 0.8267
2.250 0.3015 0.02787 0.01919 -0.0363 0.7212 0.8370
2.500 0.3331 0.02788 0.01922 -0.0372 0.7198 0.8406
2.750 0.3661 0.02785 0.01922 -0.0382 0.7186 0.8436
3.250 0.3809 0.02923 0.02069 -0.0335 0.7057 0.8543
3.500 0.4134 0.02913 0.02066 -0.0342 0.7043 0.8574
4.000 0.4379 0.03035 0.02200 -0.0310 0.6915 0.8678
4.250 0.4716 0.03019 0.02191 -0.0319 0.6897 0.8714
4.750 0.5028 0.03111 0.02302 -0.0294 0.6767 0.8822
5.000 0.5274 0.03121 0.02321 -0.0291 0.6722 0.8872
5.250 0.5401 0.03170 0.02381 -0.0275 0.6637 0.8941
5.500 0.5767 0.03122 0.02346 -0.0285 0.6611 0.8990
6.000 0.6225 0.03114 0.02363 -0.0272 0.6470 0.9126
6.500 0.6794 0.03021 0.02302 -0.0269 0.6319 0.9297
6.750 0.7001 0.03025 0.02322 -0.0265 0.6192 0.9432
7.250 0.7525 0.02969 0.02302 -0.0271 0.5922 1.0000
7.750 0.7869 0.02983 0.02335 -0.0251 0.5558 1.0000
8.000 0.8070 0.02973 0.02334 -0.0243 0.5313 1.0000
8.250 0.8340 0.02902 0.02267 -0.0236 0.4950 1.0000
8.500 0.8891 0.02582 0.01888 -0.0233 0.4033 1.0000
8.750 0.8953 0.02687 0.01943 -0.0209 0.3317 1.0000
9.000 0.8961 0.02851 0.02068 -0.0186 0.2737 1.0000
9.250 0.8994 0.03013 0.02198 -0.0167 0.2249 1.0000
9.500 0.9050 0.03168 0.02330 -0.0152 0.1839 1.0000
9.750 0.9124 0.03318 0.02458 -0.0138 0.1513 1.0000
10.000 0.9216 0.03460 0.02586 -0.0126 0.1266 1.0000
10.500 0.9400 0.03754 0.02860 -0.0104 0.0948 1.0000
10.750 0.9505 0.03896 0.03003 -0.0095 0.0839 1.0000
11.000 0.9611 0.04040 0.03150 -0.0085 0.0754 1.0000
11.250 0.9694 0.04205 0.03312 -0.0075 0.0689 1.0000
11.500 0.9813 0.04345 0.03464 -0.0067 0.0627 1.0000
11.750 0.9894 0.04519 0.03635 -0.0058 0.0576 1.0000
12.000 1.0016 0.04665 0.03795 -0.0051 0.0527 1.0000
12.250 1.0112 0.04832 0.03966 -0.0044 0.0484 1.0000
12.500 1.0213 0.05006 0.04146 -0.0037 0.0445 1.0000
12.750 1.0317 0.05178 0.04330 -0.0030 0.0404 1.0000
13.000 1.0387 0.05377 0.04530 -0.0025 0.0375 1.0000
13.250 1.0497 0.05563 0.04736 -0.0019 0.0344 1.0000
13.500 1.0582 0.05765 0.04952 -0.0014 0.0316 1.0000
13.750 1.0643 0.05985 0.05177 -0.0010 0.0296 1.0000
14.000 1.0707 0.06223 0.05426 -0.0006 0.0277 1.0000
14.250 1.0787 0.06467 0.05696 -0.0001 0.0260 1.0000
14.500 1.0846 0.06732 0.05981 0.0003 0.0248 1.0000
14.750 1.0877 0.07016 0.06281 0.0004 0.0237 1.0000
15.000 1.0893 0.07308 0.06584 0.0004 0.0228 1.0000
15.250 1.0898 0.07623 0.06905 0.0002 0.0219 1.0000
15.500 1.0867 0.08014 0.07322 -0.0001 0.0213 1.0000
15.750 1.0795 0.08459 0.07800 -0.0008 0.0206 1.0000
16.000 1.0707 0.08941 0.08313 -0.0018 0.0200 1.0000
16.250 1.0600 0.09462 0.08859 -0.0034 0.0196 1.0000
16.500 1.0468 0.10046 0.09468 -0.0055 0.0192 1.0000
16.750 1.0317 0.10693 0.10140 -0.0083 0.0191 1.0000
17.000 1.0135 0.11432 0.10903 -0.0120 0.0190 1.0000
17.250 0.9912 0.12311 0.11804 -0.0170 0.0191 1.0000
17.500 0.9615 0.13451 0.12968 -0.0239 0.0195 1.0000
17.750 0.9232 0.14971 0.14509 -0.0335 0.0202 1.0000
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