NREL's S829 Airfoil (s829-nr) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: NREL's S829 Airfoil (s829-nr) Reynolds number: 500,000 Max Cl/Cd: 62.99 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-s829-nr-500000.txt Download as CSV file: xf-s829-nr-500000.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S829 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-14.250 -0.5714 0.07596 0.07338 -0.0867 0.9400 0.0072
-14.000 -0.5902 0.06944 0.06667 -0.0903 0.9295 0.0072
-13.750 -0.6191 0.06269 0.05973 -0.0927 0.9207 0.0070
-13.500 -0.6410 0.05783 0.05466 -0.0932 0.9135 0.0069
-13.250 -0.6612 0.05363 0.05028 -0.0929 0.9069 0.0065
-13.000 -0.6862 0.04928 0.04564 -0.0911 0.9013 0.0068
-12.750 -0.7054 0.04560 0.04173 -0.0891 0.8958 0.0065
-12.500 -0.7207 0.04246 0.03833 -0.0864 0.8908 0.0063
-12.250 -0.7319 0.03978 0.03538 -0.0834 0.8864 0.0066
-12.000 -0.7395 0.03727 0.03261 -0.0805 0.8818 0.0068
-11.750 -0.7450 0.03466 0.02972 -0.0774 0.8778 0.0067
-11.500 -0.7434 0.03284 0.02764 -0.0748 0.8744 0.0069
-11.250 -0.7387 0.03078 0.02534 -0.0725 0.8713 0.0069
-11.000 -0.7292 0.02927 0.02362 -0.0707 0.8681 0.0071
-10.750 -0.7169 0.02749 0.02161 -0.0691 0.8654 0.0072
-10.500 -0.7023 0.02634 0.02029 -0.0677 0.8628 0.0073
-10.250 -0.6861 0.02523 0.01898 -0.0665 0.8605 0.0074
-10.000 -0.6680 0.02407 0.01766 -0.0655 0.8583 0.0075
-9.750 -0.6535 0.02212 0.01557 -0.0642 0.8560 0.0085
-9.500 -0.6361 0.02148 0.01488 -0.0632 0.8534 0.0090
-9.250 -0.6191 0.02069 0.01402 -0.0620 0.8509 0.0095
-9.000 -0.6025 0.01989 0.01313 -0.0606 0.8487 0.0105
-8.750 -0.5863 0.01917 0.01231 -0.0592 0.8467 0.0109
-8.500 -0.5680 0.01862 0.01168 -0.0580 0.8447 0.0118
-8.250 -0.5575 0.01744 0.01045 -0.0557 0.8424 0.0150
-8.000 -0.5394 0.01690 0.00983 -0.0545 0.8403 0.0175
-7.750 -0.5229 0.01626 0.00920 -0.0530 0.8382 0.0252
-7.500 -0.5057 0.01572 0.00867 -0.0516 0.8363 0.0337
-7.250 -0.4874 0.01528 0.00824 -0.0504 0.8346 0.0434
-7.000 -0.4692 0.01485 0.00784 -0.0492 0.8330 0.0568
-6.750 -0.4513 0.01444 0.00750 -0.0479 0.8313 0.0760
-6.500 -0.4341 0.01396 0.00716 -0.0466 0.8292 0.1016
-6.250 -0.4185 0.01345 0.00680 -0.0449 0.8271 0.1379
-6.000 -0.4046 0.01289 0.00647 -0.0430 0.8252 0.1860
-5.750 -0.3930 0.01231 0.00613 -0.0406 0.8233 0.2428
-5.500 -0.3858 0.01163 0.00575 -0.0374 0.8215 0.3133
-5.250 -0.3869 0.01083 0.00532 -0.0324 0.8196 0.3984
-5.000 -0.3966 0.01014 0.00498 -0.0255 0.8175 0.4829
-4.750 -0.4152 0.00959 0.00486 -0.0164 0.8146 0.5683
-4.500 -0.4232 0.00910 0.00494 -0.0091 0.8119 0.6837
-4.250 -0.4047 0.00918 0.00513 -0.0070 0.8102 0.7358
-4.000 -0.3835 0.00935 0.00526 -0.0056 0.8088 0.7603
-3.750 -0.3622 0.00950 0.00535 -0.0043 0.8075 0.7760
-3.500 -0.3352 0.00974 0.00556 -0.0041 0.8065 0.7872
-3.250 -0.3066 0.01003 0.00581 -0.0042 0.8056 0.7963
-3.000 -0.2827 0.01027 0.00598 -0.0034 0.8046 0.8054
-2.750 -0.2491 0.01065 0.00634 -0.0045 0.8036 0.8103
-2.500 -0.2301 0.01080 0.00644 -0.0030 0.8016 0.8179
-2.250 -0.1918 0.01132 0.00697 -0.0050 0.8006 0.8215
-2.000 -0.1571 0.01181 0.00745 -0.0063 0.7994 0.8259
-1.750 -0.1316 0.01217 0.00779 -0.0058 0.7980 0.8330
-1.500 -0.0838 0.01297 0.00860 -0.0094 0.7974 0.8351
-1.250 -0.0425 0.01346 0.00907 -0.0120 0.7966 0.8365
-1.000 -0.0083 0.01369 0.00928 -0.0134 0.7954 0.8380
-0.750 -0.0056 0.01338 0.00893 -0.0089 0.7935 0.8462
-0.500 0.0265 0.01349 0.00903 -0.0101 0.7927 0.8470
-0.250 0.0579 0.01359 0.00912 -0.0111 0.7918 0.8479
0.000 0.0893 0.01369 0.00921 -0.0120 0.7909 0.8488
0.250 0.1197 0.01382 0.00932 -0.0129 0.7900 0.8498
0.500 0.1442 0.01400 0.00955 -0.0127 0.7880 0.8515
0.750 0.1624 0.01406 0.00963 -0.0113 0.7855 0.8545
1.000 0.1663 0.01378 0.00935 -0.0072 0.7827 0.8605
1.250 0.1947 0.01380 0.00938 -0.0077 0.7812 0.8614
1.500 0.2238 0.01381 0.00942 -0.0082 0.7798 0.8623
1.750 0.2536 0.01381 0.00942 -0.0089 0.7785 0.8633
2.000 0.2834 0.01378 0.00940 -0.0096 0.7774 0.8643
2.250 0.3095 0.01378 0.00943 -0.0095 0.7754 0.8658
2.500 0.3244 0.01373 0.00943 -0.0074 0.7701 0.8689
2.750 0.3489 0.01308 0.00874 -0.0067 0.7657 0.8723
3.000 0.3784 0.01249 0.00813 -0.0070 0.7600 0.8739
3.250 0.4067 0.01216 0.00783 -0.0070 0.7534 0.8747
3.500 0.4426 0.01176 0.00740 -0.0085 0.7488 0.8752
3.750 0.4653 0.01165 0.00737 -0.0076 0.7417 0.8766
4.000 0.4958 0.01140 0.00713 -0.0082 0.7367 0.8776
4.250 0.5205 0.01128 0.00708 -0.0077 0.7310 0.8790
4.500 0.5454 0.01107 0.00692 -0.0073 0.7242 0.8805
4.750 0.5661 0.01082 0.00671 -0.0060 0.7148 0.8828
5.000 0.5851 0.01051 0.00643 -0.0044 0.7045 0.8861
5.250 0.6055 0.01030 0.00625 -0.0030 0.6931 0.8882
5.500 0.6228 0.01020 0.00624 -0.0010 0.6747 0.8896
5.750 0.6362 0.01010 0.00611 0.0020 0.6387 0.8915
6.000 0.6280 0.01026 0.00596 0.0093 0.5671 0.8953
6.250 0.6020 0.01060 0.00599 0.0196 0.5103 0.9017
6.500 0.5836 0.01139 0.00654 0.0280 0.4518 0.9056
6.750 0.5684 0.01233 0.00720 0.0352 0.3891 0.9103
7.000 0.5614 0.01324 0.00783 0.0404 0.3303 0.9149
7.250 0.5593 0.01407 0.00844 0.0450 0.2765 0.9183
7.500 0.5616 0.01488 0.00903 0.0486 0.2277 0.9216
7.750 0.5680 0.01560 0.00956 0.0514 0.1859 0.9251
8.000 0.5770 0.01628 0.01007 0.0537 0.1494 0.9284
8.250 0.5872 0.01688 0.01057 0.0558 0.1208 0.9311
8.500 0.5984 0.01748 0.01108 0.0579 0.0969 0.9342
8.750 0.6102 0.01809 0.01160 0.0598 0.0788 0.9378
9.000 0.6236 0.01865 0.01211 0.0614 0.0651 0.9412
9.250 0.6362 0.01925 0.01268 0.0631 0.0543 0.9443
9.500 0.6516 0.01976 0.01322 0.0644 0.0472 0.9474
9.750 0.6648 0.02043 0.01389 0.0660 0.0408 0.9511
10.000 0.6801 0.02093 0.01445 0.0672 0.0366 0.9550
10.250 0.6902 0.02192 0.01547 0.0689 0.0310 0.9590
10.500 0.7114 0.02234 0.01596 0.0690 0.0282 0.9624
10.750 0.7295 0.02295 0.01656 0.0694 0.0237 0.9665
11.000 0.7443 0.02392 0.01760 0.0701 0.0210 0.9704
11.250 0.7713 0.02440 0.01811 0.0688 0.0175 0.9725
11.500 0.7850 0.02596 0.01971 0.0690 0.0144 0.9752
11.750 0.8089 0.02670 0.02054 0.0681 0.0127 0.9777
12.000 0.8325 0.02737 0.02119 0.0671 0.0102 0.9805
12.250 0.8484 0.02884 0.02277 0.0668 0.0085 0.9830
12.500 0.8707 0.02994 0.02397 0.0656 0.0072 0.9844
12.750 0.8883 0.03147 0.02560 0.0649 0.0068 0.9861
13.000 0.9022 0.03326 0.02749 0.0644 0.0063 0.9878
13.250 0.9079 0.03578 0.03019 0.0648 0.0057 0.9899
13.500 0.9250 0.03721 0.03175 0.0642 0.0050 0.9924
13.750 0.9375 0.03908 0.03376 0.0637 0.0047 0.9959
14.000 0.9492 0.04121 0.03604 0.0631 0.0046 0.9991
14.250 0.9412 0.04302 0.03800 0.0661 0.0049 1.0000
14.500 0.9368 0.04457 0.03965 0.0686 0.0046 1.0000
14.750 0.9403 0.04601 0.04111 0.0696 0.0041 1.0000
15.000 0.9317 0.04924 0.04459 0.0712 0.0044 1.0000
15.250 0.9313 0.05159 0.04702 0.0717 0.0041 1.0000
15.500 0.9266 0.05461 0.05019 0.0722 0.0041 1.0000
15.750 0.9227 0.05767 0.05339 0.0723 0.0040 1.0000
16.000 0.9105 0.06202 0.05799 0.0722 0.0041 1.0000
16.250 0.9026 0.06599 0.06209 0.0715 0.0040 1.0000
16.500 0.8878 0.07122 0.06751 0.0702 0.0040 1.0000
16.750 0.8759 0.07631 0.07268 0.0683 0.0037 1.0000
17.000 0.8540 0.08357 0.08026 0.0656 0.0041 1.0000
17.250 0.8411 0.08966 0.08647 0.0625 0.0040 1.0000
17.500 0.8128 0.09920 0.09625 0.0577 0.0041 1.0000
17.750 0.7926 0.10780 0.10500 0.0529 0.0040 1.0000
18.000 0.7506 0.12198 0.11943 0.0454 0.0044 1.0000
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