NREL's S834 Airfoil (s834-nr) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S834 Airfoil (s834-nr) Reynolds number: 1,000,000 Max Cl/Cd: 102.67 at α=4° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s834-nr-1000000.txt Download as CSV file: xf-s834-nr-1000000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S834 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.9332 0.08444 0.08119 -0.0681 1.0000 0.0032
-17.500 -0.9413 0.08039 0.07708 -0.0692 1.0000 0.0033
-17.250 -0.9871 0.07060 0.06711 -0.0731 1.0000 0.0030
-17.000 -0.9989 0.06628 0.06270 -0.0743 1.0000 0.0032
-16.750 -1.0094 0.06221 0.05854 -0.0753 1.0000 0.0033
-16.500 -1.0302 0.05687 0.05308 -0.0767 1.0000 0.0033
-16.250 -1.0562 0.05120 0.04726 -0.0780 1.0000 0.0032
-16.000 -1.0723 0.04712 0.04306 -0.0784 1.0000 0.0031
-15.750 -1.0684 0.04550 0.04140 -0.0778 1.0000 0.0034
-15.500 -1.0909 0.04124 0.03700 -0.0775 1.0000 0.0033
-15.250 -1.1047 0.03764 0.03325 -0.0774 0.9997 0.0035
-15.000 -1.1008 0.03461 0.03010 -0.0794 0.9985 0.0036
-14.750 -1.0823 0.03330 0.02873 -0.0809 0.9975 0.0034
-14.500 -1.0862 0.02966 0.02493 -0.0825 0.9956 0.0041
-14.250 -1.0734 0.02780 0.02296 -0.0839 0.9944 0.0042
-14.000 -1.0544 0.02652 0.02163 -0.0853 0.9935 0.0048
-13.750 -1.0430 0.02523 0.02026 -0.0850 0.9911 0.0049
-13.500 -1.0267 0.02411 0.01905 -0.0853 0.9889 0.0053
-13.250 -1.0125 0.02264 0.01749 -0.0858 0.9868 0.0061
-13.000 -0.9927 0.02155 0.01637 -0.0866 0.9853 0.0073
-12.750 -0.9691 0.02070 0.01545 -0.0877 0.9842 0.0078
-12.500 -0.9460 0.01971 0.01439 -0.0889 0.9832 0.0090
-12.250 -0.9207 0.01887 0.01354 -0.0902 0.9823 0.0103
-12.000 -0.9099 0.01832 0.01294 -0.0881 0.9776 0.0112
-11.750 -0.8872 0.01764 0.01221 -0.0884 0.9753 0.0123
-11.500 -0.8624 0.01691 0.01147 -0.0892 0.9738 0.0145
-11.250 -0.8342 0.01636 0.01089 -0.0904 0.9727 0.0162
-11.000 -0.8057 0.01571 0.01021 -0.0918 0.9718 0.0188
-10.750 -0.7766 0.01510 0.00961 -0.0931 0.9710 0.0216
-10.500 -0.7467 0.01464 0.00911 -0.0944 0.9700 0.0239
-10.250 -0.7399 0.01422 0.00869 -0.0908 0.9636 0.0270
-10.000 -0.7171 0.01375 0.00823 -0.0905 0.9609 0.0310
-9.750 -0.6937 0.01328 0.00775 -0.0903 0.9588 0.0364
-9.500 -0.6686 0.01286 0.00734 -0.0903 0.9570 0.0417
-9.250 -0.6564 0.01252 0.00702 -0.0876 0.9515 0.0482
-9.000 -0.6356 0.01218 0.00667 -0.0866 0.9479 0.0534
-8.750 -0.6137 0.01173 0.00627 -0.0859 0.9453 0.0644
-8.500 -0.5901 0.01134 0.00591 -0.0855 0.9431 0.0735
-8.250 -0.5726 0.01107 0.00565 -0.0837 0.9382 0.0817
-8.000 -0.5514 0.01075 0.00534 -0.0827 0.9344 0.0916
-7.750 -0.5282 0.01038 0.00502 -0.0821 0.9316 0.1049
-7.500 -0.5040 0.01003 0.00471 -0.0817 0.9291 0.1184
-7.250 -0.4842 0.00976 0.00449 -0.0803 0.9241 0.1315
-7.000 -0.4609 0.00946 0.00423 -0.0797 0.9201 0.1450
-6.750 -0.4360 0.00916 0.00396 -0.0793 0.9169 0.1591
-6.250 -0.3894 0.00863 0.00352 -0.0780 0.9080 0.1930
-6.000 -0.3644 0.00836 0.00330 -0.0777 0.9041 0.2109
-5.750 -0.3383 0.00813 0.00310 -0.0776 0.9005 0.2273
-5.500 -0.3145 0.00794 0.00295 -0.0770 0.8953 0.2457
-5.250 -0.2892 0.00771 0.00277 -0.0767 0.8910 0.2653
-5.000 -0.2624 0.00750 0.00260 -0.0767 0.8872 0.2852
-4.750 -0.2379 0.00734 0.00249 -0.0762 0.8821 0.3037
-4.500 -0.2121 0.00716 0.00235 -0.0760 0.8775 0.3235
-4.250 -0.1846 0.00700 0.00222 -0.0761 0.8736 0.3447
-4.000 -0.1598 0.00685 0.00214 -0.0757 0.8686 0.3645
-3.750 -0.1337 0.00670 0.00204 -0.0755 0.8640 0.3860
-3.500 -0.1059 0.00658 0.00194 -0.0757 0.8600 0.4064
-3.250 -0.0806 0.00644 0.00188 -0.0753 0.8551 0.4276
-3.000 -0.0541 0.00633 0.00181 -0.0752 0.8503 0.4493
-2.750 -0.0266 0.00621 0.00173 -0.0753 0.8462 0.4704
-2.500 -0.0004 0.00611 0.00169 -0.0751 0.8414 0.4916
-2.250 0.0260 0.00601 0.00164 -0.0749 0.8365 0.5128
-2.000 0.0538 0.00592 0.00159 -0.0751 0.8321 0.5345
-1.750 0.0801 0.00583 0.00156 -0.0749 0.8272 0.5554
-1.500 0.1068 0.00574 0.00153 -0.0748 0.8221 0.5765
-1.250 0.1347 0.00568 0.00149 -0.0749 0.8174 0.5979
-1.000 0.1608 0.00560 0.00149 -0.0746 0.8118 0.6190
-0.500 0.2145 0.00548 0.00146 -0.0744 0.7992 0.6592
-0.250 0.2410 0.00544 0.00145 -0.0742 0.7920 0.6786
0.000 0.2679 0.00541 0.00146 -0.0740 0.7851 0.6970
0.250 0.2944 0.00538 0.00147 -0.0738 0.7776 0.7142
0.500 0.3211 0.00536 0.00149 -0.0736 0.7703 0.7302
0.750 0.3476 0.00536 0.00151 -0.0733 0.7622 0.7454
1.000 0.3741 0.00536 0.00154 -0.0730 0.7540 0.7595
1.250 0.4005 0.00539 0.00158 -0.0728 0.7458 0.7727
1.750 0.4525 0.00544 0.00168 -0.0720 0.7270 0.7960
2.000 0.4778 0.00550 0.00174 -0.0715 0.7165 0.8059
2.250 0.5030 0.00555 0.00180 -0.0709 0.7049 0.8158
2.500 0.5279 0.00563 0.00188 -0.0703 0.6928 0.8249
2.750 0.5523 0.00572 0.00197 -0.0696 0.6798 0.8328
3.000 0.5763 0.00583 0.00205 -0.0688 0.6654 0.8411
3.250 0.5987 0.00596 0.00216 -0.0676 0.6486 0.8476
3.750 0.6421 0.00627 0.00239 -0.0651 0.6117 0.8603
4.000 0.6622 0.00645 0.00253 -0.0635 0.5906 0.8664
4.250 0.6818 0.00665 0.00266 -0.0618 0.5672 0.8722
4.500 0.6968 0.00689 0.00282 -0.0592 0.5375 0.8776
4.750 0.7090 0.00720 0.00298 -0.0560 0.5011 0.8839
5.000 0.7210 0.00754 0.00319 -0.0528 0.4612 0.8891
5.250 0.7335 0.00795 0.00346 -0.0498 0.4220 0.8948
5.500 0.7461 0.00842 0.00374 -0.0470 0.3782 0.9005
5.750 0.7583 0.00885 0.00403 -0.0440 0.3396 0.9055
6.000 0.7728 0.00927 0.00432 -0.0416 0.3044 0.9110
6.250 0.7870 0.00969 0.00459 -0.0391 0.2711 0.9161
6.500 0.7993 0.01014 0.00491 -0.0363 0.2354 0.9215
6.750 0.8134 0.01061 0.00524 -0.0339 0.2034 0.9270
7.000 0.8273 0.01096 0.00551 -0.0314 0.1801 0.9322
7.250 0.8415 0.01136 0.00582 -0.0290 0.1581 0.9379
7.500 0.8565 0.01172 0.00612 -0.0269 0.1396 0.9433
7.750 0.8693 0.01210 0.00644 -0.0243 0.1205 0.9496
8.000 0.8819 0.01259 0.00681 -0.0218 0.0977 0.9561
8.250 0.8950 0.01297 0.00715 -0.0193 0.0831 0.9636
8.500 0.9111 0.01342 0.00755 -0.0176 0.0684 0.9713
8.750 0.9324 0.01396 0.00803 -0.0171 0.0541 0.9789
9.000 0.9576 0.01458 0.00856 -0.0176 0.0409 0.9867
9.250 0.9821 0.01505 0.00902 -0.0178 0.0347 1.0000
9.500 1.0004 0.01560 0.00954 -0.0168 0.0280 1.0000
9.750 1.0176 0.01621 0.01010 -0.0157 0.0223 1.0000
10.000 1.0365 0.01671 0.01062 -0.0148 0.0193 1.0000
10.250 1.0527 0.01739 0.01128 -0.0135 0.0157 1.0000
10.500 1.0706 0.01795 0.01188 -0.0125 0.0143 1.0000
10.750 1.0863 0.01864 0.01255 -0.0112 0.0118 1.0000
11.000 1.1019 0.01933 0.01327 -0.0100 0.0094 1.0000
11.250 1.1158 0.02015 0.01410 -0.0085 0.0083 1.0000
11.500 1.1282 0.02106 0.01506 -0.0069 0.0069 1.0000
11.750 1.1427 0.02184 0.01588 -0.0055 0.0063 1.0000
12.000 1.1571 0.02261 0.01670 -0.0043 0.0062 1.0000
12.250 1.1687 0.02359 0.01771 -0.0028 0.0055 1.0000
12.500 1.1749 0.02497 0.01918 -0.0007 0.0047 1.0000
12.750 1.1860 0.02601 0.02029 0.0008 0.0046 1.0000
13.000 1.1969 0.02708 0.02142 0.0021 0.0045 1.0000
13.250 1.2082 0.02814 0.02254 0.0034 0.0042 1.0000
13.500 1.2175 0.02937 0.02384 0.0047 0.0042 1.0000
13.750 1.2256 0.03071 0.02525 0.0061 0.0040 1.0000
14.000 1.2327 0.03217 0.02679 0.0074 0.0040 1.0000
14.250 1.2397 0.03369 0.02838 0.0087 0.0038 1.0000
14.500 1.2456 0.03533 0.03010 0.0098 0.0037 1.0000
14.750 1.2488 0.03727 0.03212 0.0110 0.0036 1.0000
15.000 1.2522 0.03925 0.03419 0.0120 0.0036 1.0000
15.250 1.2562 0.04125 0.03629 0.0128 0.0036 1.0000
15.500 1.2585 0.04347 0.03860 0.0135 0.0035 1.0000
15.750 1.2603 0.04583 0.04104 0.0140 0.0035 1.0000
16.000 1.2587 0.04866 0.04397 0.0145 0.0034 1.0000
16.250 1.2557 0.05177 0.04720 0.0146 0.0034 1.0000
16.500 1.2554 0.05468 0.05020 0.0145 0.0034 1.0000
16.750 1.2454 0.05891 0.05457 0.0141 0.0033 1.0000
17.000 1.2365 0.06322 0.05901 0.0134 0.0033 1.0000
17.250 1.2243 0.06822 0.06415 0.0121 0.0032 1.0000
17.500 1.2191 0.07244 0.06847 0.0108 0.0032 1.0000
17.750 1.2135 0.07688 0.07303 0.0091 0.0032 1.0000
18.000 1.2033 0.08222 0.07850 0.0070 0.0032 1.0000
18.250 1.1840 0.08928 0.08572 0.0039 0.0032 1.0000
18.500 1.1779 0.09437 0.09091 0.0013 0.0032 1.0000
18.750 1.1608 0.10156 0.09825 -0.0022 0.0032 1.0000
19.000 1.1531 0.10723 0.10402 -0.0053 0.0032 1.0000
19.250 1.1396 0.11408 0.11100 -0.0090 0.0033 1.0000
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