NREL's S832 Airfoil (s832-nr) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S832 Airfoil (s832-nr) Reynolds number: 200,000 Max Cl/Cd: 67.2 at α=7° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s832-nr-200000-n5.txt Download as CSV file: xf-s832-nr-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S832 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.000 0.0048 0.09321 0.08864 -0.1243 0.8106 0.0183
-9.750 0.0075 0.09037 0.08579 -0.1261 0.8071 0.0184
-9.500 0.0099 0.08738 0.08280 -0.1280 0.8037 0.0186
-9.250 0.0131 0.08440 0.07984 -0.1297 0.7998 0.0186
-9.000 0.0149 0.08118 0.07663 -0.1317 0.7962 0.0187
-8.750 0.0179 0.07808 0.07352 -0.1335 0.7930 0.0187
-8.500 0.0193 0.07480 0.07024 -0.1358 0.7899 0.0187
-8.250 0.0165 0.07123 0.06669 -0.1386 0.7855 0.0188
-8.000 0.0141 0.06835 0.06379 -0.1395 0.7817 0.0188
-7.750 0.0105 0.06584 0.06121 -0.1395 0.7784 0.0188
-7.500 0.0108 0.06289 0.05819 -0.1398 0.7755 0.0188
-7.250 0.0128 0.06005 0.05529 -0.1398 0.7720 0.0188
-7.000 0.0169 0.05722 0.05236 -0.1395 0.7688 0.0188
-6.500 0.0239 0.04989 0.04487 -0.1382 0.7636 0.0135
-6.250 0.0309 0.04764 0.04256 -0.1375 0.7607 0.0128
-6.000 0.0391 0.04486 0.03965 -0.1367 0.7573 0.0122
-5.750 0.0489 0.04172 0.03631 -0.1355 0.7544 0.0113
-5.250 0.0753 0.03484 0.02879 -0.1324 0.7498 0.0105
-5.000 0.0935 0.03328 0.02704 -0.1319 0.7479 0.0112
-4.750 0.1106 0.03137 0.02492 -0.1305 0.7447 0.0124
-4.500 0.1292 0.02860 0.02176 -0.1286 0.7418 0.0133
-4.250 0.1490 0.02642 0.01926 -0.1274 0.7393 0.0131
-4.000 0.1713 0.02436 0.01686 -0.1264 0.7371 0.0129
-3.750 0.1957 0.02243 0.01456 -0.1256 0.7354 0.0128
-3.500 0.2219 0.02079 0.01256 -0.1250 0.7338 0.0128
-3.250 0.2446 0.01954 0.01110 -0.1240 0.7311 0.0130
-3.000 0.2682 0.01852 0.00990 -0.1231 0.7284 0.0134
-2.750 0.2917 0.01763 0.00891 -0.1223 0.7260 0.0142
-2.500 0.3156 0.01703 0.00828 -0.1218 0.7238 0.0152
-2.250 0.3403 0.01653 0.00769 -0.1213 0.7219 0.0177
-2.000 0.3661 0.01619 0.00733 -0.1212 0.7203 0.0233
-1.750 0.3885 0.01592 0.00706 -0.1205 0.7180 0.0315
-1.500 0.4098 0.01573 0.00688 -0.1196 0.7153 0.0442
-1.250 0.4327 0.01552 0.00664 -0.1190 0.7129 0.0591
-1.000 0.4566 0.01525 0.00643 -0.1186 0.7107 0.0886
-0.750 0.4589 0.01329 0.00664 -0.1142 0.7085 0.7309
-0.500 0.4785 0.01346 0.00687 -0.1118 0.7068 0.8182
-0.250 0.4988 0.01367 0.00701 -0.1096 0.7052 0.8522
0.000 0.5120 0.01397 0.00732 -0.1065 0.7021 0.8744
0.250 0.5270 0.01419 0.00753 -0.1036 0.6995 0.8915
0.500 0.5444 0.01433 0.00764 -0.1011 0.6973 0.9067
0.750 0.5664 0.01441 0.00764 -0.1000 0.6953 0.9170
1.000 0.5947 0.01442 0.00756 -0.1004 0.6936 0.9196
1.250 0.6245 0.01443 0.00748 -0.1012 0.6922 0.9218
1.500 0.6487 0.01456 0.00757 -0.1009 0.6901 0.9252
1.750 0.6655 0.01480 0.00782 -0.0993 0.6870 0.9305
2.000 0.6880 0.01496 0.00798 -0.0988 0.6845 0.9345
2.250 0.7139 0.01507 0.00808 -0.0989 0.6824 0.9381
2.500 0.7415 0.01514 0.00812 -0.0993 0.6806 0.9417
2.750 0.7705 0.01519 0.00813 -0.0999 0.6790 0.9454
3.000 0.8025 0.01524 0.00816 -0.1012 0.6778 0.9482
3.250 0.8241 0.01555 0.00852 -0.1007 0.6752 0.9536
3.500 0.8422 0.01591 0.00895 -0.0996 0.6718 0.9606
3.750 0.8705 0.01613 0.00920 -0.1004 0.6693 0.9648
4.000 0.9008 0.01627 0.00937 -0.1016 0.6674 0.9693
4.250 0.9329 0.01639 0.00951 -0.1030 0.6658 0.9738
4.500 0.9685 0.01647 0.00962 -0.1052 0.6645 0.9771
4.750 1.0047 0.01653 0.00971 -0.1074 0.6633 0.9807
5.000 1.0195 0.01727 0.01060 -0.1064 0.6584 0.9988
5.250 1.0290 0.01760 0.01099 -0.1036 0.6549 1.0000
5.500 1.0524 0.01773 0.01116 -0.1034 0.6527 1.0000
5.750 1.0821 0.01776 0.01123 -0.1042 0.6509 1.0000
6.000 1.1171 0.01767 0.01119 -0.1059 0.6493 1.0000
6.250 1.0954 0.01871 0.01232 -0.0978 0.6411 1.0000
6.500 1.1325 0.01823 0.01188 -0.0995 0.6373 1.0000
6.750 1.1355 0.01858 0.01229 -0.0956 0.6287 1.0000
7.000 1.1793 0.01755 0.01124 -0.0980 0.6210 1.0000
7.250 1.1683 0.01856 0.01236 -0.0922 0.6115 1.0000
7.500 1.1929 0.01847 0.01232 -0.0919 0.6053 1.0000
7.750 1.1946 0.01931 0.01326 -0.0883 0.5970 1.0000
8.000 1.2092 0.01969 0.01372 -0.0867 0.5894 1.0000
8.250 1.2229 0.02012 0.01422 -0.0850 0.5809 1.0000
8.500 1.2248 0.02119 0.01540 -0.0819 0.5702 1.0000
8.750 1.2340 0.02192 0.01621 -0.0798 0.5585 1.0000
9.000 1.2429 0.02271 0.01707 -0.0777 0.5448 1.0000
9.250 1.2528 0.02345 0.01786 -0.0757 0.5277 1.0000
9.500 1.2660 0.02398 0.01839 -0.0741 0.5048 1.0000
9.750 1.2808 0.02426 0.01852 -0.0724 0.4637 1.0000
10.000 1.2809 0.02547 0.01942 -0.0691 0.4143 1.0000
10.250 1.2701 0.02761 0.02126 -0.0650 0.3696 1.0000
10.500 1.2598 0.02995 0.02339 -0.0613 0.3314 1.0000
10.750 1.2512 0.03238 0.02562 -0.0582 0.2969 1.0000
11.000 1.2431 0.03490 0.02797 -0.0554 0.2626 1.0000
11.250 1.2395 0.03723 0.03017 -0.0531 0.2341 1.0000
11.500 1.2376 0.03952 0.03234 -0.0512 0.2081 1.0000
12.000 1.2391 0.04385 0.03651 -0.0480 0.1629 1.0000
12.250 1.2416 0.04597 0.03858 -0.0467 0.1438 1.0000
12.500 1.2454 0.04801 0.04059 -0.0456 0.1274 1.0000
12.750 1.2502 0.05000 0.04255 -0.0446 0.1120 1.0000
13.000 1.2552 0.05202 0.04456 -0.0437 0.0977 1.0000
13.250 1.2604 0.05405 0.04658 -0.0428 0.0850 1.0000
13.500 1.2653 0.05615 0.04867 -0.0421 0.0726 1.0000
13.750 1.2704 0.05828 0.05080 -0.0413 0.0621 1.0000
14.000 1.2750 0.06046 0.05300 -0.0407 0.0529 1.0000
14.250 1.2791 0.06278 0.05532 -0.0400 0.0448 1.0000
14.500 1.2845 0.06497 0.05760 -0.0395 0.0382 1.0000
14.750 1.2887 0.06736 0.06005 -0.0390 0.0332 1.0000
15.000 1.2915 0.06994 0.06266 -0.0386 0.0280 1.0000
15.250 1.2955 0.07242 0.06525 -0.0382 0.0240 1.0000
15.500 1.2963 0.07533 0.06820 -0.0379 0.0205 1.0000
15.750 1.3003 0.07790 0.07090 -0.0377 0.0172 1.0000
16.000 1.3004 0.08100 0.07403 -0.0377 0.0146 1.0000
16.250 1.3041 0.08370 0.07684 -0.0377 0.0116 1.0000
16.500 1.3047 0.08681 0.08004 -0.0378 0.0094 1.0000
16.750 1.3047 0.09008 0.08343 -0.0380 0.0080 1.0000
17.000 1.3026 0.09372 0.08718 -0.0384 0.0071 1.0000
17.250 1.3024 0.09713 0.09075 -0.0388 0.0056 1.0000
17.500 1.2997 0.10101 0.09479 -0.0395 0.0054 1.0000
17.750 1.2950 0.10523 0.09915 -0.0403 0.0048 1.0000
18.000 1.2955 0.10871 0.10276 -0.0413 0.0036 1.0000
18.250 1.2910 0.11303 0.10722 -0.0425 0.0034 1.0000
18.500 1.2852 0.11769 0.11206 -0.0439 0.0028 1.0000
18.750 1.2796 0.12240 0.11695 -0.0455 0.0028 1.0000
19.000 1.2739 0.12721 0.12193 -0.0474 0.0026 1.0000
19.250 1.2674 0.13229 0.12718 -0.0496 0.0025 1.0000
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