NREL's S820 Airfoil (s820-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S820 Airfoil (s820-nr) Reynolds number: 100,000 Max Cl/Cd: 39.31 at α=9° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s820-nr-100000.txt Download as CSV file: xf-s820-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S820 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 -0.3624 0.10582 0.10192 -0.0629 0.9763 0.1143
-10.000 -0.3150 0.10381 0.09986 -0.0592 0.9740 0.1227
-9.750 -0.4460 0.10501 0.10091 -0.0533 0.9877 0.1089
-9.500 -0.4667 0.09778 0.09371 -0.0624 0.9837 0.1126
-9.250 -0.4996 0.09283 0.08874 -0.0663 0.9777 0.1132
-9.000 -0.5284 0.08918 0.08502 -0.0687 0.9728 0.1134
-8.750 -0.4945 0.08487 0.08079 -0.0692 0.9717 0.1229
-8.500 -0.5280 0.08237 0.07827 -0.0672 0.9649 0.1230
-8.250 -0.5538 0.07975 0.07555 -0.0663 0.9597 0.1246
-8.000 -0.5859 0.07799 0.07366 -0.0625 0.9544 0.1264
-7.750 -0.6321 0.07816 0.07334 -0.0578 0.9479 0.1287
-5.000 -0.5250 0.04462 0.03633 -0.0371 0.9253 0.0574
-4.750 -0.5045 0.04203 0.03344 -0.0356 0.9243 0.0508
-4.500 -0.4831 0.04156 0.03240 -0.0336 0.9228 0.0475
-4.250 -0.4592 0.03976 0.03039 -0.0329 0.9209 0.0477
-4.000 -0.6153 0.03993 0.03152 -0.0049 1.0000 0.0543
-3.750 -0.5910 0.03858 0.02950 -0.0029 1.0000 0.0478
-3.500 -0.5698 0.03700 0.02772 -0.0019 1.0000 0.0480
-3.250 -0.5482 0.03576 0.02630 -0.0008 1.0000 0.0478
-3.000 -0.5265 0.03490 0.02526 0.0003 1.0000 0.0472
-2.750 -0.5049 0.03375 0.02404 0.0014 1.0000 0.0467
-2.500 -0.4839 0.03276 0.02303 0.0025 1.0000 0.0465
-2.250 -0.4632 0.03195 0.02223 0.0037 1.0000 0.0471
-2.000 -0.4430 0.03089 0.02128 0.0046 0.9997 0.0488
-1.750 -0.4158 0.03059 0.02096 0.0039 0.9972 0.0522
-1.500 -0.3858 0.03058 0.02086 0.0027 0.9947 0.0646
-1.250 -0.3600 0.02815 0.02022 0.0011 0.9943 0.4159
-1.000 -0.3731 0.03045 0.02398 0.0151 0.9890 0.7666
-0.750 -0.3789 0.03277 0.02643 0.0268 0.9840 0.8240
-0.500 -0.3908 0.03316 0.02688 0.0379 0.9778 0.8634
-0.250 -0.3813 0.03431 0.02794 0.0437 0.9724 0.8950
0.000 -0.3607 0.03417 0.02758 0.0433 0.9670 0.8997
0.250 -0.3275 0.03484 0.02806 0.0406 0.9604 0.9025
0.500 -0.3022 0.03523 0.02830 0.0394 0.9560 0.9058
0.750 -0.2732 0.03561 0.02853 0.0376 0.9478 0.9097
1.000 -0.2434 0.03652 0.02929 0.0354 0.9433 0.9141
1.250 -0.2177 0.03660 0.02928 0.0342 0.9339 0.9175
1.500 -0.1842 0.03775 0.03033 0.0314 0.9292 0.9213
1.750 -0.1582 0.03790 0.03039 0.0301 0.9188 0.9261
2.000 -0.1328 0.03847 0.03091 0.0289 0.9121 0.9312
2.250 -0.0938 0.03959 0.03196 0.0253 0.9028 0.9357
2.500 -0.0724 0.03976 0.03209 0.0247 0.8926 0.9413
2.750 -0.0332 0.04118 0.03348 0.0209 0.8860 0.9460
3.000 0.0079 0.04216 0.03444 0.0171 0.8733 0.9509
3.250 0.0716 0.04160 0.03379 0.0126 0.8206 0.9536
3.500 0.1293 0.04177 0.03393 0.0080 0.7962 0.9578
3.750 0.1830 0.04239 0.03456 0.0030 0.7858 0.9614
4.000 0.2163 0.04272 0.03494 0.0006 0.7731 0.9671
4.250 0.2532 0.04318 0.03545 -0.0024 0.7611 0.9726
4.500 0.2965 0.04368 0.03602 -0.0062 0.7499 0.9774
4.750 0.3531 0.04398 0.03639 -0.0114 0.7425 0.9822
5.000 0.3927 0.04431 0.03681 -0.0148 0.7298 0.9879
5.250 0.4322 0.04461 0.03723 -0.0180 0.7178 0.9961
5.500 0.4525 0.04439 0.03707 -0.0175 0.7071 1.0000
5.750 0.4893 0.04374 0.03649 -0.0186 0.6996 1.0000
6.000 0.5074 0.04353 0.03635 -0.0178 0.6869 1.0000
6.250 0.5351 0.04329 0.03620 -0.0183 0.6748 1.0000
6.500 0.5698 0.04280 0.03582 -0.0194 0.6637 1.0000
6.750 0.6266 0.04115 0.03436 -0.0222 0.6572 1.0000
7.000 0.6597 0.04034 0.03368 -0.0227 0.6446 1.0000
7.250 0.6958 0.03925 0.03276 -0.0234 0.6324 1.0000
7.500 0.7368 0.03765 0.03134 -0.0241 0.6210 1.0000
7.750 0.7993 0.03423 0.02818 -0.0259 0.6151 1.0000
8.000 0.8365 0.03221 0.02639 -0.0257 0.6017 1.0000
8.250 0.8764 0.02979 0.02419 -0.0254 0.5867 1.0000
8.500 0.8973 0.02888 0.02343 -0.0237 0.5606 1.0000
8.750 0.9258 0.02743 0.02210 -0.0224 0.5215 1.0000
9.000 0.9733 0.02476 0.01889 -0.0215 0.4233 1.0000
9.250 0.9774 0.02598 0.01940 -0.0184 0.3417 1.0000
9.500 0.9777 0.02772 0.02064 -0.0155 0.2861 1.0000
9.750 0.9822 0.02942 0.02196 -0.0134 0.2449 1.0000
10.000 0.9910 0.03098 0.02324 -0.0117 0.2139 1.0000
10.250 1.0030 0.03245 0.02453 -0.0104 0.1885 1.0000
10.500 1.0187 0.03388 0.02577 -0.0095 0.1677 1.0000
10.750 1.0323 0.03534 0.02723 -0.0085 0.1496 1.0000
11.000 1.0469 0.03682 0.02869 -0.0076 0.1336 1.0000
11.250 1.0617 0.03840 0.03025 -0.0067 0.1186 1.0000
11.500 1.0760 0.04006 0.03192 -0.0058 0.1052 1.0000
11.750 1.0905 0.04188 0.03377 -0.0050 0.0927 1.0000
12.000 1.1038 0.04381 0.03576 -0.0041 0.0818 1.0000
12.250 1.1197 0.04591 0.03790 -0.0034 0.0720 1.0000
12.500 1.1319 0.04794 0.04001 -0.0025 0.0644 1.0000
12.750 1.1442 0.05076 0.04312 -0.0014 0.0579 1.0000
13.000 1.1528 0.05287 0.04523 -0.0006 0.0524 1.0000
13.250 1.1607 0.05669 0.04943 0.0006 0.0491 1.0000
13.500 1.1555 0.05983 0.05295 0.0025 0.0464 1.0000
13.750 1.1539 0.06226 0.05550 0.0036 0.0432 1.0000
14.000 1.1590 0.06684 0.06013 0.0040 0.0404 1.0000
14.250 1.1432 0.07077 0.06443 0.0055 0.0400 1.0000
14.500 1.1243 0.07505 0.06907 0.0066 0.0396 1.0000
14.750 1.1046 0.07984 0.07417 0.0070 0.0394 1.0000
15.000 1.0843 0.08484 0.07946 0.0068 0.0393 1.0000
15.250 1.0590 0.09067 0.08557 0.0059 0.0390 1.0000
15.500 1.0389 0.09668 0.09179 0.0043 0.0395 1.0000
15.750 1.0165 0.10330 0.09861 0.0019 0.0397 1.0000
16.000 0.9919 0.11077 0.10626 -0.0015 0.0399 1.0000
16.250 0.9734 0.11820 0.11381 -0.0050 0.0404 1.0000
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Polar data table (+)
Polar graphs
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