NREL's S826 Airfoil (s826-nr) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S826 Airfoil (s826-nr) Reynolds number: 100,000 Max Cl/Cd: 60.86 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s826-nr-100000.txt Download as CSV file: xf-s826-nr-100000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S826 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
------ -------- --------- --------- -------- -------- --------
-9.500 -0.3634 0.11434 0.10974 -0.0423 1.0000 0.0929
-9.250 -0.3916 0.11175 0.10730 -0.0455 1.0000 0.0942
-9.000 -0.4179 0.10881 0.10449 -0.0476 1.0000 0.0946
-8.750 -0.3700 0.10518 0.10078 -0.0403 1.0000 0.0991
-8.500 -0.3723 0.10284 0.09848 -0.0392 1.0000 0.1026
-8.250 -0.3868 0.10021 0.09596 -0.0392 1.0000 0.1061
-8.000 -0.4201 0.09768 0.09360 -0.0404 1.0000 0.1081
-7.750 -0.4587 0.09530 0.09138 -0.0403 1.0000 0.1086
-7.500 -0.4321 0.09243 0.08851 -0.0358 1.0000 0.1125
-7.250 -0.4370 0.09088 0.08702 -0.0330 1.0000 0.1154
-7.000 -0.4578 0.08924 0.08550 -0.0306 1.0000 0.1177
-6.500 -0.4922 0.07565 0.07200 -0.0507 0.9900 0.1265
-6.250 -0.4704 0.06759 0.06372 -0.0658 0.9790 0.1409
-6.000 -0.4425 0.06326 0.05939 -0.0702 0.9722 0.1576
-5.750 -0.4186 0.05983 0.05598 -0.0730 0.9630 0.1768
-5.500 -0.3272 0.04224 0.03553 -0.0979 0.9596 0.0553
-5.250 -0.2854 0.03984 0.03258 -0.1011 0.9517 0.0533
-5.000 -0.2410 0.03610 0.02844 -0.1052 0.9472 0.0527
-4.750 -0.2011 0.03312 0.02512 -0.1077 0.9411 0.0522
-4.500 -0.1595 0.03108 0.02274 -0.1098 0.9349 0.0538
-4.250 -0.1233 0.02904 0.02080 -0.1117 0.9290 0.0625
-4.000 -0.0881 0.02749 0.01938 -0.1126 0.9220 0.0735
-3.750 -0.0508 0.02641 0.01841 -0.1142 0.9149 0.0951
-3.500 0.0123 0.02443 0.01790 -0.1230 0.9102 0.4728
-3.250 0.0264 0.02680 0.02041 -0.1166 0.8985 0.5152
-3.000 0.0477 0.02854 0.02220 -0.1113 0.8918 0.5449
-2.750 0.0642 0.02940 0.02300 -0.1076 0.8806 0.5650
-2.500 0.0832 0.02998 0.02350 -0.1043 0.8713 0.5805
-2.250 0.1091 0.03029 0.02374 -0.1018 0.8653 0.5965
-2.000 0.1335 0.03037 0.02371 -0.1009 0.8560 0.6098
-1.750 0.1657 0.03008 0.02332 -0.1007 0.8511 0.6176
-1.500 0.2065 0.02947 0.02251 -0.1047 0.8447 0.6201
-1.250 0.2505 0.02876 0.02161 -0.1092 0.8389 0.6212
-1.000 0.3043 0.02779 0.02043 -0.1154 0.8362 0.6229
-0.750 0.3382 0.02742 0.01996 -0.1173 0.8291 0.6249
-0.500 0.3766 0.02694 0.01940 -0.1196 0.8238 0.6274
-0.250 0.4262 0.02625 0.01861 -0.1240 0.8212 0.6303
0.000 0.4574 0.02617 0.01846 -0.1258 0.8135 0.6329
0.250 0.5039 0.02568 0.01786 -0.1303 0.8090 0.6365
0.500 0.5522 0.02506 0.01718 -0.1345 0.8060 0.6402
0.750 0.5729 0.02532 0.01745 -0.1339 0.7970 0.6432
1.000 0.6148 0.02499 0.01709 -0.1369 0.7929 0.6470
1.250 0.6648 0.02449 0.01653 -0.1417 0.7901 0.6516
1.500 0.6806 0.02504 0.01711 -0.1406 0.7805 0.6550
1.750 0.7202 0.02476 0.01685 -0.1427 0.7767 0.6593
2.000 0.7404 0.02531 0.01745 -0.1424 0.7690 0.6635
2.250 0.7792 0.02525 0.01737 -0.1452 0.7639 0.6684
2.500 0.8189 0.02497 0.01714 -0.1473 0.7606 0.6726
2.750 0.8295 0.02587 0.01813 -0.1452 0.7514 0.6770
3.000 0.8721 0.02567 0.01796 -0.1483 0.7472 0.6834
3.250 0.8862 0.02639 0.01880 -0.1465 0.7393 0.6875
3.500 0.9202 0.02641 0.01889 -0.1479 0.7339 0.6930
3.750 0.9545 0.02651 0.01907 -0.1494 0.7285 0.6991
4.000 0.9724 0.02709 0.01979 -0.1482 0.7204 0.7044
4.250 1.0200 0.02660 0.01934 -0.1514 0.7159 0.7127
4.500 1.0292 0.02745 0.02038 -0.1487 0.7058 0.7179
4.750 1.0724 0.02697 0.01998 -0.1510 0.6994 0.7262
5.000 1.0938 0.02721 0.02037 -0.1499 0.6893 0.7325
5.250 1.1217 0.02726 0.02057 -0.1498 0.6793 0.7412
5.500 1.1665 0.02636 0.01974 -0.1516 0.6706 0.7505
5.750 1.1878 0.02653 0.02008 -0.1504 0.6587 0.7597
6.000 1.2131 0.02648 0.02018 -0.1496 0.6467 0.7700
6.250 1.2410 0.02619 0.02005 -0.1489 0.6344 0.7803
6.500 1.2704 0.02580 0.01979 -0.1485 0.6214 0.7923
6.750 1.2977 0.02540 0.01953 -0.1476 0.6072 0.8059
7.000 1.3214 0.02502 0.01933 -0.1461 0.5914 0.8213
7.250 1.3429 0.02460 0.01907 -0.1442 0.5741 0.8392
7.500 1.3631 0.02407 0.01869 -0.1419 0.5552 0.8615
7.750 1.3784 0.02347 0.01824 -0.1387 0.5354 0.8952
8.000 1.3901 0.02312 0.01810 -0.1354 0.5101 1.0000
8.250 1.4071 0.02312 0.01818 -0.1336 0.4753 1.0000
8.500 1.4116 0.02346 0.01851 -0.1296 0.4279 1.0000
8.750 1.4068 0.02426 0.01892 -0.1239 0.3634 1.0000
9.000 1.3952 0.02608 0.02017 -0.1180 0.3038 1.0000
9.250 1.3838 0.02833 0.02199 -0.1128 0.2571 1.0000
9.500 1.3751 0.03071 0.02406 -0.1084 0.2202 1.0000
9.750 1.3692 0.03313 0.02623 -0.1047 0.1914 1.0000
10.000 1.3663 0.03556 0.02846 -0.1016 0.1675 1.0000
10.250 1.3658 0.03797 0.03070 -0.0990 0.1475 1.0000
10.500 1.3680 0.04042 0.03296 -0.0968 0.1303 1.0000
10.750 1.3720 0.04278 0.03530 -0.0948 0.1148 1.0000
11.000 1.3770 0.04519 0.03768 -0.0931 0.1012 1.0000
11.250 1.3831 0.04767 0.04014 -0.0915 0.0889 1.0000
11.500 1.3898 0.05024 0.04264 -0.0901 0.0774 1.0000
11.750 1.3923 0.05281 0.04535 -0.0887 0.0685 1.0000
12.000 1.4003 0.05562 0.04828 -0.0873 0.0596 1.0000
12.250 1.4109 0.05853 0.05120 -0.0862 0.0521 1.0000
12.500 1.4186 0.06139 0.05422 -0.0850 0.0467 1.0000
12.750 1.4285 0.06485 0.05781 -0.0840 0.0417 1.0000
13.000 1.4312 0.06824 0.06149 -0.0828 0.0386 1.0000
13.250 1.4368 0.07168 0.06508 -0.0820 0.0362 1.0000
13.500 1.4418 0.07663 0.07020 -0.0813 0.0339 1.0000
13.750 1.4281 0.08102 0.07502 -0.0806 0.0331 1.0000
14.000 1.4144 0.08582 0.08019 -0.0804 0.0322 1.0000
14.250 1.3998 0.09101 0.08572 -0.0808 0.0316 1.0000
14.500 1.3836 0.09660 0.09162 -0.0817 0.0311 1.0000
14.750 1.3660 0.10269 0.09801 -0.0833 0.0309 1.0000
15.000 1.3469 0.10931 0.10493 -0.0857 0.0310 1.0000
15.250 1.3259 0.11655 0.11244 -0.0889 0.0311 1.0000
15.500 1.3040 0.12440 0.12054 -0.0930 0.0314 1.0000
15.750 1.2823 0.13281 0.12915 -0.0979 0.0320 1.0000
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